Abstract: An aircraft landing gear includes a leg having a strut receiving a telescopic rod to slide on a sliding axis, the strut being hinged to an aircraft structure and being capable of pivoting about a pivot axis that is highly offset from the sliding axis. The landing gear further includes a connection structure essentially formed by two panels connecting two axially separate points of the strut to a common axis structure extending along the strut pivot axis. In the gear-down position, the panels are one above the other, the top panel being connected to the strut via a high attachment which is rigid in twisting, while the bottom panel is connected to the strut via a low attachment which tolerates twisting, thereby enabling the strut to warp to some extent when the aircraft is turning while taxiing.

Abstract: The invention relates to aircraft landing gear of the type comprising a leg constituted by a strut receiving a telescopic rod to slide on a sliding axis, said strut being hinged to an aircraft structure and being capable of pivoting about a pivot axis that is highly offset from the sliding axis. In accordance with the invention, the landing gear includes a connection structure essentially constituted by two panels connecting two axially separate points of the strut to a common axis structure extending along the strut pivot axis. In the gear-down position, the panels are one above the other, the top panel being connected to the strut via a high attachment which is rigid in twisting, while the bottom panel is connected to the strut via a low attachment which tolerates twisting, thereby enabling the strut to warp to some extent when the aircraft is turning while taxiing.

Abstract: An aircraft landing gear includes a leg having a strut receiving a telescopic rod to slide on a sliding axis, the strut being hinged to an aircraft structure and being capable of pivoting about a pivot axis that is highly offset from the sliding axis. The landing gear further includes a connection structure essentially comprising two panels connecting two axially separate points of the strut to a common axis structure extending along the strut pivot axis. In the gear-down position, the panels are one above the other, the top panel being connected to the strut via a high attachment which is rigid in twisting, while the bottom panel is connected to the strut via a low attachment which tolerates twisting, thereby enabling the strut to warp to some extent when the aircraft is turning while taxiing.

Abstract: The invention relates to aircraft landing gear of the type comprising a leg (11) constituted by a strut (12) receiving a telescopic rod (13) to slide on a sliding axis (Z), said strut being hinged to an aircraft structure and being capable of pivoting about a pivot axis (X) that is highly offset from the sliding axis (Z). In accordance with the invention, the landing gear (10) includes a connection structure (100) essentially constituted by two panels (101, 102) connecting two axially separate points of the strut (12) to a common axis structure (103) extending along the strut pivot axis (X). In the gear-down position, the panels (101, 102) are one above the other, the top panel (101) being connected to the strut (12) via a high attachment (105) which is rigid in twisting, while the bottom panel (102) is connected to the strut (12) via a low attachment (106) which tolerates twisting, thereby enabling the strut (12) to warp to some extent when the aircraft is turning while taxiing.

Abstract: The process of the invention is a process for selective hydrogenation of a hydrocarbon feed containing hydrogen and C2+ hydrocarbons, characterized in that it comprises at least one step for separating a fraction of the hydrogen contained in the feed by means of a membrane (step a)) and a step for selective hydrogenation of the effluent from step a) in a reactive column (step b)).

Abstract: The process of the invention is a process for selective hydrogenation of a hydrocarbon feed containing hydrogen and C2+ hydrocarbons, characterized in that it comprises at least one step for separating a fraction of the hydrogen contained in the feed by means of a membrane (step a)) and a step for selective hydrogenation of the effluent from step a) in a reactive column (step b)).

Abstract: The invention relates to aircraft landing gear of the type that is laterally-raisable and that has twin wheels in a side-by-side configuration. According to the invention, the leg is constituted by an upside-down L-shaped strut whose two branches are hinged together, comprising a beam-forming first branch that is hinged to the structure of the aircraft and a second branch having a wheel lever hinged to the end thereof. The wheel lever is also connected to the first branch via a shock absorber. A controlling guide bar connects the second branch to the structure of the aircraft via a fork swivel-mounted on said second branch, in such a manner as to cause said second branch to move forwards while the landing ger is being raised, such forwards movement causing the wheels to be folded in because the shock absorber then acts as a second guide bar.

Abstract: The invention relates to a raisable undercarriage comprising a hinged leg and associated bracing means. According to the invention, the undercarriage is of the leg-shortening type, and the bracing means are organized in the form of a foldable brace having its bottom arm hinged to bottom end of the sliding rod of the hinged leg, said brace further being organized so that, in the undercarriage down position, the lowered leg slopes towards the front of the aircraft.

Abstract: The strut of the leg has a lateral extension on its outside above the rotary sleeve, the cylinder of a steering actuator is suspended from the lateral extension by means of a universal joint, the end of the rod off said actuator is hinged to a lateral steering lug of the rotary sleeve. This flexible disposition puts fewer constraints on implementation of the scissor linkage, and it improves guidance of the rotary sleeve.

Abstract: A linear actuator, in particular for driving an aircraft landing gear leg, the actuator comprising a main body with a screw that is prevented from moving axially and that is constrained to rotate with a coaxial gear wheel that meshes with the outlet gear wheel of a driving motor and gear box assembly, and a nut that is secured to a sliding guide rod inside said main body. According to the invention, the rotary connection between the screw and the coaxial gear wheel is provided by declutchable coupling means, which means is declutched in an emergency for the purpose of releasing the screw by associated trigger means whose operation requires very little energy.

Abstract: The running gear comprises a tilting beam having one end hinged to the vehicle about a tilt pin and supporting a rotary axle for at least one wheel, a blade spring having a first end fixed to the vehicle and a second end hinged to a first end of a shock absorber having a second end hinged to the vehicle, and a control actuator hinged firstly to the second end of the blade spring and secondly to a tilting control pin carried by the tilting beam at a point that is spaced apart from the tilting pin in order to control the tilt of the tilting beam.

Abstract: The invention relates to raisable landing gear including a shock absorbing leg that is pivotally mounted, and to a driving actuator associated therewith. According to the invention, the leg is implemented in the form of two elements that are hinged to each other about an axis parallel to the pivot axis of the leg and that are connected together by means of a shock absorber, the bottom element forming a rocker and the top element forming a panel whose free end is connected to a drive actuator which is a shock-absorbing actuator having a force threshold, said shock-absorbing actuator serving to apply a predetermined torque that maintains the leg in position during normal landing, while allowing said leg to be raised against a controlled force in the event of a crash landing.

Abstract: The invention relates to an oscillating arm suspension assembly for a heavy vehicle, in particular for a track vehicle. According to the invention, the oscillating arm comprises a housing receiving firstly a shock absorber of the type in which a semi-solid elastomer is hydrostatically compressed, said shock absorber being mounted coaxially about the oscillation axis of said arm, and secondly an oleo-pneumatic spring of the two-chamber type, having a hydraulic chamber closed by a sliding piston with a piston rod hinged thereto whose end opposite from the piston is hinged to a fixed member inside said housing.

Abstract: The invention relates to a shock absorber for a landing gear leg, the shock absorber being of the type comprising a cylinder and a sliding rod, and including a disk that delimits a lower hydraulic fluid chamber which communicates via a diaphragm with an upper hydraulic fluid chamber adjacent to a pressurized gas chamber formed in the top portion of the cylinder. According to the invention, the sliding rod 102 is implemented in telescopic form, having an outer rod 131 and an inner rod 132 which bears directly against an intermediate partition 112 constituting the above-mentioned disk when the shock absorber is relaxed or under static load. The shock absorber also includes a linear actuator 150.1 received in the inner rod 132, and which, when triggered, serves to extend the landing gear providing the airplane is stationary or is moving slowly on the ground. Two scissors linkages 124 and 127 are also provided for conveying structural twisting forces.

Abstract: The invention relates to a shock absorber of the type comprising a cylinder and a sliding rod, together with a moving disk that defines a bottom hydraulic chamber that communicates via a diaphragm with a top hydraulic fluid chamber that is adjacent to a pressurized gas chamber formed in the top of the cylinder. According to the invention, a self-contained linear actuator is disposed coaxially inside the sliding rod, being interposed between the moving disk and a lower abutment secured to said sliding rod, independent control means being also provided to control the linear actuator, such that when said means are engaged they enable the landing gear to be extended when the aircraft is stationary on the ground.

Abstract: The invention relates to a shock-absorbing actuator including a cylindrical body and a hollow rod having an annular piston. The cylindrical body includes a separator piston delimiting two hydraulic fluid chambers, one of which communicates via a distributor valve with the hydraulic circuit of the aircraft, said distributor valve being closed automatically at the end of lowering the landing gear; the annular chamber communicates via a second distributor valve with said hydraulic circuit. The distributor valves thus make it possible to extend and retract the shock-absorbing actuator. In addition, a force peak-limiting means is disposed in an extension extending beyond an end wall of the body that forms one of the abutments for the separator piston.

Abstract: The invention relates to a catch device of the type comprising a main casing that houses a hinge hook and a locking lever having one branch carrying a thrust wheel that co-operates with the hook and having its other branch connected by means of a linkage to the outlet from a driving motor and gear box assembly. According to the invention, the linkage (112) includes an oblong slot (122) for enabling the locking lever (106) to pivot in the event of the outlet shaft (113) of the motor and gear box assembly being jammed, and, in addition, an independent trigger (130) is associated with the locking lever (106) so that when triggered in an emergency it causes said lever to pivot far enough to disengage thrust wheel (109) from the associated camming surface (110.1) of the hinged hook (102), thereby releasing it.

Abstract: The invention relates to a shock absorber comprising a main body and a rod-piston, with the rod-piston being retracted when the landing gear is down and extended when the landing gear is up. The main body comprises, in succession, three chambers that are separated by associated partitions, and that comprise: a first hydraulic chamber in which the rod-piston slides freely; a chamber in which a separator piston slides, delimiting a second hydraulic chamber; and a chamber in which another piston slides, delimiting both a third hydraulic chamber and a chamber containing gas under high pressure. Communication means are provided between said chambers together with two associated electrically controlled valves enabling corresponding fluid connections to be selectively established.

Abstract: The shock absorber comprises a strut, a sliding rod slidably mounted relative to the strut and co-operating therewith to define both a shock absorbing chamber and a raising chamber which is connected to a member for feeding it with raising liquid, a dip tube defining a lowering chamber and connected to a member for feeding it with a lowering liquid, and in which a lowering piston is disposed, which piston has one face in contact with the shock absorbing liquid, and an anti-crash tube mounted to slide relative to the sliding rod and including an energy-absorbing member.

Abstract: The invention relates to raisable landing gear including a shock absorber having a strut and a sliding rod, together with a two-alignment hinged side-brace. According to the invention, unlocking means are provided to break the secondary alignment, thereby breaking the main alignment while the landing gear is being raised, said means being essentially constituted by a lever mounted to rotate on one of the arms of the main alignment, and by a motor and gear box assembly for driving said rotary lever in rotation and further including an unlocking arm that, when said motor and gear box assembly is in action, co-operates with the lower arm of the secondary alignment to break said secondary alignment. Return means are also associated with the rotary lever to ensure that it returns to its initial position when the landing gear is raised.