Abstract: The safety lock comprises a control member which prevents an untimely actuation of the jettisoning device by inserting a locking member on the path of a movable release member of this device. Simultaneously the safety lock releases braking members in order to allow nuts to rotate for ensuring the raising of the hooks to which the load is suspended.

Abstract: A device for suspending and wedging loads under aircraft ensures, through a central control, the wedging of a load carried under an aircraft at a level determined by a pair of suspension hooks subjected to balanced stresses. The central control is obtained by sleeves which slide vertically under the action of rotary shafts and bevel-tooth gears, the vertical translation of these sleeves ensuring the downward movement of parts of bearings engaging the load.

Abstract: This device with independent hooks and automatic locking mechanism for hooking loads suspended under aircraft comprises an effort scaling-down device associated with each hook, mechanisms for coupling the two scaling-down mechanisms with each other, and the detent-positioning of this coupling mechanism through the medium of a third common scaling-down device. Thus, the preliminary manual cocking, i.e. the detent-positioning of the coupling, provides at the same time the simultaneous resetting of the first pair of effort scaling-down mechanisms associated therewith, so that the suspension hooks are free with respect to the retaining mechanism and can pivot to their closed position independently of each other under the action of the load suspension rings when the load is fixed in position, the third scaling-down device further assisting in reducing the efforts exerted on the common retaining pawl, the raising of this common pawl being necessarily attended by the simultaneous opening of the hook.

Abstract: This device for transporting and jettisoning ringless loads, notably under aircraft, comprises at least one pair of gripping arms operable about two substantially perpendicular axes. Each gripping arm is associated with a separate universal joint structure, the two structures being assembled by a cross member. A structure is provided for locking the gripping arms in their retracted position.

Abstract: This device for locking on fixed support loads carried under aircraft comprises, between the suspension rings or saddles of the load and the fixed structure of the aircraft, a pair of spaced pivot pins having fulcrumed thereon a pair of symmetrically opposed bell-crank levers having in turn one arm pivotally connected to a suspension hook and the other arm pivotally connected to a common stretching device, the fulcri of the levers having each also pivoted thereto a radial link having its free end pivoted to a pair of links connected the one to a central rocker and the other to the relevant hook, the rocker being responsive to a detent-positioning device.

Abstract: This device incorporated in a release or ejector mechanism for adjusting the transverse direction of an airborne load comprises a device for pivoting thereon the load-supporting hook and a bell crank linkage system, whether the load is equipped with a so-called saddle member or with standard rings. This device comprises essentially a cylindrical body formed either with an eccentric portion or with a transverse screw for performing the necessary adjustment, and a lock nut for firmly maintaining the selected adjustment position.

Abstract: This automatic wedging device for operating each ejector of loads carried under an aircraft for jettisoning comprises at least one actuator of the cylinder-and-piston or worm-and-wheel type adapted to transmit a wedging force to a pair of symmetrical load-engaging wedging levers, and a device for automatically operating each actuator when the load is properly positioned in relation to the aircraft; other devices are provided for locking the wedging levers when this force has attained a predetermined value and restoring the wedging levers to their inoperative position after the load has been jettisoned as a consequence of the opening of the load suspension hooks.

Abstract: This hoisting device for loads to be carried under aircraft is incorporated partially or completely in a load carrier system without requiring any lateral access, the connection between the hoisting device and the load being eliminated automatically once the load is properly anchored to the carrier system. The device comprises one or two ropes, as the case may be, and comprises an anchoring member rigid with the load and formed with an internal groove engageable by a set of balls carried by a socket in which an end piece crimped to the rope end is adapted to travel axially through a limited extent. Slackening the rope will free the load which is then retained by the carrier system.

Abstract: This device for automatically and releasably hanging and holding loads carried under aircraft against lateral oscillation incorporates a push member and a ball and socket of which the line of action with respect to the load is directed slightly outside the transverse dimension of the associated bridge member engaged by substantially triangular sockets of the ball and socket to prevent any lateral oscillation of the load under centrifugal or transverse aerodynamic or inertia forces.

Abstract: An ejector serves for suspending under aircraft loads which have suspension rings or saddle members, both of known kind. The ejector includes a carrier device which has, for each load suspension point, a first pivoted hook which can coact with a saddle member, a fastener disposed adjacent to the first hook, and a detachable device removably mounted in the fastener, the detachable device having a housing for receiving the upper part of a suspension ring, a second hook pivotable about a horizontal pin and serving, in a closed position, to lock the suspension ring in the housing, and a spring urging the second hook against the first hook so that the second hook follows opening and closing movements of the first hook and is itself thereby moved into opening and closing positions.

Abstract: In a telescopic retractable ejector, the driving gas is allowed to flow freely with the maximum efficiency by compensating the pressure drop resulting from the gas expansion during the piston extension with a concomitant and automatic increment in the surface area of the pistons which is exposed to the gas pressure.

Abstract: This pressure control device, more particularly for use in pyrotechnical load ejectors of the type used for jettisoning loads on aircrafts, comprises an easily detachable block consisting of a main body and of detachable component elements secured to the main body, the latter comprising a bore for the sliding mounting of a spool valve urged by a return spring for automatically limiting the downstream pressure delivered to the pyrotechnical impellers mounted in cavities of the main body, other component elements secured laterally to the body permitting when removed an easy access to the gas passages for cleaning purposes.

Abstract: A system for securing under an aircraft a jettisonable load having either a known suspension ring or a known suspension bridge with laterally spaced recesses. The carrier structure on the aircraft includes a withdrawable pivot pin for supporting a hook which can be removed and turned through 180.degree. for presenting optionally a single projection to engage with a suspension ring, or a pair of abutments to engage in the recesses of a suspension bridge. The hook is releasably angularly coupled to an actuating shank pivotable about the pin.

Abstract: This device for automatically releasably hanging and holding against lateral oscillation load carried under aircrafts has load suspension hooks and holding members preventing the lateral oscillation of the load which project very moderately from the underface of a closed casing containing the actuating mechanism. This mechanism includes in combination linkage detents and springloaded devices disposed on either side of each load suspension hook. A certain delay is introduced into the action whereby when the load is lifted for engagement with the hooks, these are actuated to their load-supporting position and release with a predetermined time-lag the linkage holding the load against lateral oscillation to their operative position. To this end, each pivotally mounted hook is connected via a spring-loaded piston-and-cylinder actuator to a rocker controlling the movement of wedge members controlling in turn a lever supporting the holding members.