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 absorbing the kinetic energy resulting from the relative motion between two bodies comprises a tubular test-element attached to one body and a pressure member rigid with the other body and contacting a suitable longitudinal profile of the test-tube, so that during the relative movement of the two bodies the movement of the pressure member, for example in the form of a carriage provided with pairs of rollers, is attended by a plastic deformation of the cross-sectional contour of the test-tube.

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 device for jettisoning a load in two completely different ways comprises a rocker fulcrumed on a support rigid with the load, or spherical member formed integrally with the support, and a pair of opposed hooks fulcrumed to the structure from which the load is to be suspended, these hooks being responsive to separate control members, so that when only one hook is retracted the load can be released. If a spherical member is used, sliding cylindrical members having opposed ends formed with spherical concavities matching the curvature of the spherical member are provided, so that retracting one or both sliding members will release the load.

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 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 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: This device for locking the door of an enclosure notably for housing safety equipments on aircraft or the like comprises means permitting of opening notwithstanding the additional load resulting from the use of a stronger opening spring than in hitherto known devices of this character, without modifying the external shape and dimensions of the device nor increasing the consumption of electric current for energizing the means provided for releasing the device to its open condition, whereby the device remains completely interchangeable with prior art devices not provided with the complemental features of this invention, consisting essentially in the use of a coil spring having several arms and possibly also of an intermediate lever for increasing the lever advantage of hitherto known single-lever devices.

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 automatic release and ejection locking mechanism for said equipment boxes, notably for aircraft comprises locking balls releasable from their locked condition by means of a piston constantly urged by a coiled compression spring to its release position. The locking means are held against the force of the ejection spring by means of an effort scalingdown device, so that the force to be applied to said device for keeping the locking action may be very moderate and the release can be obtained by reducing or cancelling the low retaining force exerted on the effort scaling-down device, for example by means of electromagnetic release means, in combination or not with a permanent magnet. (FIG.

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: Device for memorizing the position of a counting system in case of failure or cut-off in the supply current characterized by the combination of a magnetic doughnut with each output of said counter, said doughnut being adapted to be energized by a pair of windings supplied with current under the control of the associated counter output so as to assume one or the other of two states according to the momentary state of the associated counter output, said doughnut further comprising a third winding delivering or not, when the supply current is restored, a pulse utilized for restoring the counter to the state it had when the cut-off took place.

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.

Abstract: This electromechanical device with a manual emergency control for opening the door of a safety outfit box on board an aircraft comprises in said box a spring-loaded piston responsive to an electromagnet and having a head shaped to control the movements of registering locking members into or out from their locking position in which they engage a retaining hook engageable in turn with a cross member of a strap carried by the door. Said locking members may consist of balls or small ball-bearings engageable in corresponding holes formed in a sleeve concentric to said piston. Manual control means are provided for actuating said piston from the outside and thus opening the door in case of emergency.

Abstract: This device for steadying, notably against lateral oscillation, a load releasably suspended from an aircraft comprises spring urged wedge members mounted to the load; these wedge members in their steading position penetrate between the upper face of the load and the lower face of the carrier member of the aircraft; these wedge members are retracted manually against the force of their spring means to allow the suspension of the load.

Abstract: This device for the remote transmission of a plurality of orders through a single control line or channel is intended more particularly for controlling the firing rates and volley-firing limitation of rockets or miscellaneous cartridges notably on aircraft. It comprises essentially a selector-switch control unit and a receiver unit. The device is energized from the common direct-current supply of the aircraft.