Abstract: A method of minimizing the consequences of an off-specification landing for the occupants of an aircraft (1) having a rotary wing (10) and a fuselage (7) extending along a longitudinal anteroposterior plane of symmetry (4) between a first side (5) and a second side (6) of said aircraft (1), said aircraft having landing gear provided with at least first contact means (21) connected by a first fastener device (30) to the fuselage and at least second contact means (22) connected by a second fastener device (50) to the fuselage, the first contact means and the first fastener device being arranged on said first side (5), the second contact means and the second fastener device being arranged on said second side (6). The fastener elements of said first and second fastener devices (30, 50) are then dimensioned differently.

Abstract: Surface-area safety means (10) comprising a barrier net (20) and at least one fastener means (30), each fastener means (30) having a fastener strap (40) fastened to a segment (25) of said barrier net (20) and co-operating with a fastener member (50) suitable for fastening said fastener strap (40) to said structure (2). The fastener means (30) also include a tensioning strap (60) fastened thereto, said tensioning strap (60) including at least two tensioning eyelets (61), said fastener strap (40) having a securing system (200) for securing it to a tensioning eyelet (61) and securing the fastener strap (40) to the tensioning strap (60) by passing through a particular tensioning eyelet in order to tension said barrier net (20) to the tension corresponding to the particular tensioning eyelet.

Abstract: Aircraft landing gear (10) provided with at least one contact means (20) for making contact with a contact surface (S). The landing gear includes energy absorber means (30) provided with an inflatable airbag (31) secured to said contact means (20), said energy absorber means (30) being provided with control means (32) and with at least one inflation means (32) for inflating said airbag (31) under the control of said control means (32), said energy absorber means (30) including adjuster means (34) for adjusting the pressure that exists inside (INT) said airbag (31).

Abstract: An aircraft undercarriage is provided (1). The undercarriage (1) includes a rocker lever (2) having a first end zone (2a) for fastening to at least one point of the structure of the aircraft and a second end zone (2b) connected via a swivel (3) to twin wheels (4) including a wheel axle (9) connecting together two landing wheels (R1, R2). The swivel (3) includes a first portion (3b) that is fastened to the second end zone (2b) of the rocker lever (2) and a second portion (3c) being free to swivel relative to the first portion (3b) about a swivel axis (A1, A2) of the swivel (3). the second portion (3c) is connected to the wheel axle (9) of the twin wheels (4). In addition, the connection between the second portion (3c) of the swivel (3) and the wheel axle (9) includes a hinge (6).

Abstract: A method of determining the locations of loads in a vehicle in such a manner as to ensure mission safety in terms of loads being retained in the aircraft. On the basis of vehicle parameters, the anchor points available in this type of vehicle for retaining the loads are identified. As a function of the available loading volume(s), a possible loading configuration is calculated using at least some of the available anchor points, at least some of the retaining means, and the characteristics of the loads. The forces that might be exerted on the selected anchor points are verified as being less than maximum limits. The calculated loading configuration is confirmed, otherwise a new loading configuration is calculated.

Abstract: A method of determining the locations of loads in a vehicle in such a manner as to ensure mission safety in terms of loads being retained in the aircraft. On the basis of vehicle parameters, the anchor points available in this type of vehicle for retaining the loads are identified. As a function of the available loading volume(s), a possible loading configuration is calculated using at least some of the available anchor points, at least some of the retaining means, and the characteristics of the loads. The forces that might be exerted on the selected anchor points are verified as being less than maximum limits. The calculated loading configuration is confirmed, otherwise a new loading configuration is calculated.

Abstract: Aircraft landing gear (10) provided with at least one contact means (20) for making contact with a contact surface (S). The landing gear includes energy absorber means (30) provided with an inflatable airbag (31) secured to said contact means (20), said energy absorber means (30) being provided with control means (32) and with at least one inflation means (32) for inflating said airbag (31) under the control of said control means (32), said energy absorber means (30) including adjuster means (34) for adjusting the pressure that exists inside (INT) said airbag (31).

Abstract: The invention relates to an aircraft undercarriage (1), the undercarriage (1) comprising a rocker lever (2) having a first end zone (2a) for fastening to at least one point of the structure of the aircraft and a second end zone (2b) connected via a swivel (3) to twin wheels (4) comprising a wheel axle (9) connecting together two landing wheels (R1, R2), said swivel (3) presenting a first portion (3b) that is fastened to said second end zone (2b) of the rocker lever (2) and a second portion (3c) presenting freedom to swivel relative to the first portion (3b) about a swivel axis (A1, A2) of said swivel (3), said second portion (3c) being connected to said wheel axle (9) of the twin wheels (4). In addition, the connection between the second portion (3c) of said swivel (3) and said wheel axle (9) presents a hinge (6).

Abstract: The device comprises a rigid former reproducing the volume of a portion of the body and suitable for receiving the compressive orthosis. The former (10) incorporates a plurality of sensors (22) distributed over various points of the former and configured in such a manner as to avoid significantly modifying the surface profile of the former, the sensors essentially measuring the pressure applied locally on the former by the orthosis at the location of the sensor and perpendicularly to the surface of the former. Advantageously, at the location of the measurement point, each sensor comprises a thin wall capable of being subjected to microdeformation under the effect of the pressure applied by the orthosis, and means such as a strain gauge bridge, for example. The thin wall can constitute a portion of a support pellet which is fitted to the former in such a manner that its outside surface, which includes the thin wall, is flush with the outside surface of the former.

Abstract: Helicopter landing gear, comprising two skids P each having a longitudinal support stretch 1 for standing on the ground and which are connected to a front cross-piece and a rear cross-piece 2 which are themselves attached to the structure of the aircraft by connecting devices 4, 6, the rear cross-piece 2 being fixed by the ends of its descending branches 2a to the rear part of the said longitudinal support stretches 1. Each of the said skids P has at the front an inclined transition zone T with double curvature C1, C2 orienting itself transversely with respect to the said longitudinal support stretches which stand on the ground, above the plane of the latter, the two transition zones together constituting in this way an integrated front cross-piece offset with respect to the front delimitation of the plane of contact of the said longitudinal support stretches of the skids on the ground.Application to light helicopters.

Abstract: A multi-layer fabric having greatly improved tearing resistance is obtained for canopies and tarpaulins and the like by the provision of two-layers of a woven textile fabric positioned on either side of a deformable reinforcing layer formed from wires having a high mechanical strength. The textile layers are bonded to the deformable reinforcing layer by a layer of material having a modulus of elasticity in shear allowing it to break when a force is exerted on the reinforcing wires, thus permitting movement of the wires within the fabric without breaking under the action of the force. Adhesive bonding layers join the outer fiber woven textile material to each other and to the wire loop layer to form a unified fabric structure. Thus, when it is attempted to cut or tear the fabric with a sharp instrument drawn across the surface thereof, the looped wires are displaced and bear successively against one another offering increased resistance until they stop the knife without breaking or tearing further.

Abstract: A device for covering or uncovering a surface by a cover comprising at least one fixed rigid supporting rod placed close to the surface to be covered, a driving member, a helical screw co-axial to the supporting rod and of which one end is connected to the driving member, a rigid pin connected to the cover to be folded or unfolded and held between the supporting rod and the co-axial helical screw, the rigid pin being designed to slide along the screw.

Abstract: In an angled connection in accordance with the invention, the one-way flow of fluid at a restricted flow rate is provided in a direction opposite to direction F by co-operation between a wall (23) having fixed orifices and a plug (26) having moving openings (31). The area of overlap between the fixed orifices through the wall (23) and the moving openings (31) is adjustable by rotating the plug (26). Flow in the opposite direction, i.e. the direction of arrow F, is provided at full flow rate by openings (22) provided through the plug (26), which openings are closed by a non-return valve (37) which allows flow in said direction F. The plug (26) and the wall (23) are pressed together in sealed manner by a resilient member (33). The plug (26) is rotated by an outside ring (38) on the tubular portion (5) of the connection, said ring being coupled to the plug via a slot through the tubular portion (5), which slot is isolated in sealed manner from the path of fluid flow through the connection.

Abstract: An assembly of operational connections for a pneumatic jack, having combined mounting for ensuring at least two operations. A first operational connection (1) ensuring the operation of regulating the discharge from the jack is provided beyond its endwall (4) which is pierced with a hole (5), with an assembly collar (6) in which is mounted a second operational connection (15) which ensures any other desired operation, arranged perpendicularly to the first operational connection (1) and equipped with a common projecting threaded ferrule (19) for the mounting of the assembly upon a jack cylinder.

Abstract: Stage for a system for distributing pneumatic control signals by electrical means, comprising a large number of associated stages. Each stage comprises a removable electrical valve (141) having an electro-magnet (33) of very low power, and a fixed socket (5) into which it fits: a pneumatic amplifier (57) is housed in the body (51), of the socket and feeds relatively large amounts of fluid to an outlet connector (26) when it is activated by the outlet of a low flow pneumatic switch (40); a non-return valve (88) protects the amplifier against pressure perturbations in the discharge duct (4). Numerous thin stages of a thickness close to 17.5 mm. can with advantage be used as an interface between a pneumatic installation (28) and a control center (24) supplying low level electrical signals.

Abstract: A system is provided using a multiplicity of coupled modules (43) each module comprising a removable electro-magnetic valve (53) provided with terminals (73, 74) and a base (52) having coupling members (106, 107) which cooperate with the terminals, and connecting pieces (104, 123) for supplying the coil (55). This system is applicable in particular in industrial installations where electrical detectors control pneumatic apparatus.

Abstract: A switch provides for cutting the pressure feed for distributors placed downstream of it, and for coupling the feed of these distributors to an exhaust of the switch itself, and has faces for connection with faces of the distributors, channels for circulation of exhaust fluid, members for connection with adjacent distributors, and is adapted for mounting on a conventional profiled element. The switch is particularly advantageous for ensuring the control of the feed of one or of several jacks coupled to distributors.

Abstract: A progressive pneumatic starter device delivers at its outlet an increasing pressure of low flow rate, then a working pressure at a high flow rate. The starter device is provided with a distributor member adapted to connect, in parallel with a calibrated bore, a channel of large section, when a pressure which is greater than a predetermined threshold and which is not derived from the outlet is applied to the distributor member. The starter device is advantageously placed upstream of a pneumatic switch to which it is directly associated for the purpose of shortening its channels for transfer of fluid.

Abstract: In an auxiliary control device for a pneumatic distributor the improvement is the integration, in a housing of the body of the distributor closed by a stopper, of a commutator sub-assembly placed on each control channel, thereby making it possible to obtain its actuation by a manual handle, by an electromagnet or by a pneumatic actuator, without necessitating the manipulation of delicate elements.

Abstract: In a process for impregnating a reel of thread in the form of a spool with a liquid resin composition, the thread is arranged on a perforated rigid mandrel so as to form a uniform reel in which the volume of open space approximately corresponds to the desired volume of resin to be impregnated, each spool is then gripped and completely sealed against resin leakage from its ends and, finally, the composition is injected under pressure into the interior of the perforated mandrel whereby there is a homogeneous loss of pressure from the mandrel to the spool's entire exterior curved surface and the resin diffuses uniformly to fill all voids through the spool.