Abstract: A connector tool assembly for compressing solar panel connectors together includes a pair of pliers and a pair of members that is each coupled to a jaw associated with a respective one of the pliers. A pair of grips is provided and each of the grips is coupled to a respective one of the members. Each of the grips has a slot extending therethrough to accommodate a conductor of a respective one of a pair of solar panel connectors having the solar panel connectors positioned between the grips. Each of the grips is urged toward each other when the pair of pliers is manipulated into a closed position. In this way each of the grips compresses the solar panel connectors into a connected condition.

Abstract: A deployable grille with fins for a thrust-reversal system for an aircraft turbine engine. The grille can adopt a rest position and a deployed, active position wherein the fins are axially spaced further apart than in the rest position. At least between two fins, the grille includes resilient return device forcing the two fins to move apart axially from one another.

Abstract: An aircraft propulsion unit comprising an engine and a nacelle including an axisymmetric casing (16) delimiting an air flow path, wherein this casing has at least two openings closed by removable and interchangeable panels (18), at least one of these panels carrying one component (24) of the propulsion unit.

Abstract: An aeronautic engine including: a housing made of electrically insulating material and including at least one metallic piece; a structural piece of the engine including metallic material and connected to the housing; and an equipment fixed to the housing, is provided. The equipment is connected to the structural piece by the metallic piece by an electrically conductive connecting path.

Abstract: A deployable grille with fins for a thrust-reversal system for an aircraft turbine engine. The grille can adopt a rest position and a deployed, active position wherein the fins are axially spaced further apart than in the rest position. At least between two fins, the grille includes resilient return device forcing the two fins to move apart axially from one another.

Abstract: Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterized in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Abstract: An arrangement of a tank of lubrication liquid for an aircraft turbomachine, under a nacelle cowling covering the turbomachine, is provided. The tank is arranged in the volume located between the turbomachine and the nacelle cowling. The nacelle cowling includes an opening for access to the volume. The tank is fastened to an internal face of a panel closing off the opening. The unit formed by the panel and the tank is added onto the nacelle cowling and is able to be mounted and dismounted from the nacelle cowling.

Abstract: Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterised in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Abstract: An aircraft propulsion unit comprising an engine and a nacelle including an axisymmetric casing (16) delimiting an air flow path, wherein this casing has at least two openings closed by removable and interchangeable panels (18), at least one of these panels carrying one component (24) of the propulsion unit.

Abstract: The invention relates to an aeronautic engine (1), comprising: a housing (10), made of electrically insulating material, said housing (10) comprising at least one metallic piece (16a, 16b, 17, 18), a structural piece (2) of the engine (1), comprising metallic material (2, 3) and connected to the housing (10), and an equipment (30), fixed to the housing (10), the aeronautic engine (1) being characterized in that the equipment is connected to the structural piece (2) by means of the metallic piece (16a, 16b, 17, 18) by means of an electrically conductive connecting path (20, 22).

Abstract: The invention proposes an arrangement of a tank of lubrication liquid for an aircraft turbomachine (12), under a nacelle cowling (10) covering said turbomachine (12), with the tank being arranged in the volume located between the turbomachine (12) and the nacelle cowling (10), with the nacelle cowling (10) comprising an opening (22) for access to said volume, characterised in that the tank (18) is fastened to an internal face (20a) of a panel (20) closing off said opening (22), with the unit formed by the panel (20) and the tank being added onto the nacelle cowling (10) and able to be mounted and dismounted from the nacelle cowling (10).

Abstract: An intermediate casing for a turbojet fan compartment, including: a shroud centered along a longitudinal axis of the turbine engine; an annular cheek plate centered along the longitudinal axis of the turbine engine and mounted against a downstream face of the shroud; a suspension beam fastened to the cheek plate and extending downstream parallel to the longitudinal axis of the turbine engine; and an AGB suspended from the beam and including an upstream side face spaced apart axially from the cheek plate, a downstream side face opposite the upstream side face, and a plurality of accessories mounted against its downstream side face and distributed about the longitudinal axis of the turbine engine.

Abstract: A by-pass turbojet including a thrust reverser is disclosed. The thrust reverse includes a deflector device which deflects all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector device is inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.

Abstract: A client device receives a broadcast content signal containing an interactive identifier over a managed network at a client device. The interactive identifier may be a trigger that is included in a header or embedded within the digital video data. The trigger may have a temporal component, wherein the trigger can expire after a certain period of time. In response to identification of the trigger, the client device sends a user request for interactive content over an unmanaged network. For example, the managed network may be a one-way satellite television network, IP-television network or cable television network and the unmanaged network may be the Internet. The client device switches between receiving data from the managed network to receiving data from the unmanaged network.

Abstract: A method, system, and computer program product for providing a decoy identifier, such as an MPEG PID, for a non-encrypted component. By obscuring the true identifier, an MPEG receiver that can decode ‘clear channels’ can not locate, and therefore, can not decode and present the true component for the program to a display device. By using the disclosed methodology, computer program product and system a cable television system or other provider of individualized content can broadcast a requested component without needing to encrypt the component.

Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.

Abstract: Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.

Abstract: A by-pass turbojet including a thrust reverser. The thrust reverse comprises deflector means for deflecting all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector means are inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.

Abstract: Efficient messaging techniques that facilitate interactive program guide (IPG) delivery and allow a terminal to specifically designate requested items of information from a server. The IPG can be provided via a number of IPG pages, with each page including a number of defined regions. In one method, selection for a particular region of a particular page is received at a terminal and a determination is made whether the selected region is currently received. If the answer is no, a request for the selected region is generated and sent to a server. The request can conform to a particular message format that includes a number of fields, e.g., a region ID field that identifies the selected region, a subtype field that identifies a particular type, a time slot field that identifies a specific time slot, and a page offset field that identifies a specific page from among many.

Abstract: An apparatus for providing multiple session-based services at a terminal, an exemplary apparatus includes a memory configured to support a plurality of software layers including a service layer communicating with terminal resources via a root layer disposed therebetween; and a processor, for executing instructions associated with a plurality of service layer applications, a root layer application and a control mechanism; each of the service layer applications communicating with terminal resources to provide thereby a respective user interface; wherein the control mechanism selectively causing at least one of the service layer applications to enter an active state, the user interface associated with a service layer application being adapted in response to the service layer application entering the active state.