Abstract: A guide height adjuster comprises a block consisting of a plurality of steps of different heights integrally joined together and having a slot formed to allow the passage of a screw across all the steps, a guide holder having a through hole for the insertion of the screw, and a guide to formed as to cover substantially a channel through which components being handled pass, the guide being secured to, and supported by, the guide holder. The guide holder rests on one of the steps and is fastened to the block by the screw so that the guide can be held above the channel. The height of the guide above the channel can be changed by loosening the screw and moving the block with respect to the screw, thereby shifting the guide holder to another block step of a desired height.

Abstract: A hoist is provided for an aircraft, such as a helicopter or VTOL, capable of hovering flight and has a boom pivotally connected to the structural frame of the aircraft for movement between retracted and extended positions. A cable powered by a winch is engaged with the boom and is used with the extended boom for conventional hoisting operations. The arrangement of the cable guide pulleys relative to the pivot axis of the boom and the operation of the winch control system is such that the cable and winch are additionally usable to effect movement of the boom between its retracted and extended positions thereby eliminating the need for a separate boom extending and retracting motor.

Abstract: Flight control system for aircraft of the type provided with ailerons, elevators, upper surface spoilers, and upper surface air-brakes, a rudder and horizontal stabilizers with variable angle of incidence, said system comprising an electric control, in some cases without any mechanical emergency control for said upper surface spoilers and air-brakes.According to the invention:the ailerons and elevators are electrically controlled without any mechanical aid,the rudder is mechanically controlled, andthe horizontal stabilizers with variable angle of incidence are electrically controlled with mechanical aid.the electrical flight controls are optimized.

Abstract: A ram air turbine and deployment mechanism has commonly had power-generating means in the form of either one, or both, of a hydraulic pump and electrical generator mounted at the end of a pivotal strut adjacent the ram air turbine. Relocation of the power-generating means can provide a system with improved operation, lesser weight and other improvements over prior known systems.The ram air turbine is mounted at the end of a pivotal strut for movement between stowed and deployed positions. The electrical generator forms a major part of the strut and is located close to the pivot axis of the strut. The hydraulic pump is mounted to aircraft structure within the stowing compartment of the aircraft and has a driven member aligned with the pivot axis of the pivotal strut.

Abstract: An easily assembled, steerable two-string kite suitable for sailing in light or strong winds having self-adjusting wing members, a substantially delta-shaped frame made of lightweight material and covered with flexible sail material capable of in-flight maneuvers including maintaining constant speed over a wide angle relative to the ground, direct overhead flight, 90-degree turns relative to the center of the kite, and lift-off from the ground, all without need to adjust or alter the position of the strings affixed to the kite.

Abstract: A deicer control circuit wherein a pressurized air source is connected to control valves and a regulating valve. Such regulating valve has a vacuum line output line that is also connected to such control valves. The control valves, on actuation by a timer, will sequence the pressure line and the vacuum line to alternately inflate and deflate the deicer units. The control valves also provide a sealing off or locking in of the pressurized deicer units in this sequence in response to a pressure sensor.

Abstract: For controlling nutation of a three-axis stabilized satellite, the angular speed of a solar panel carried by the satellite is selectively and temporarily varied about an average value for modifying the inertia cross-product thereof and generating an angular momentum transverse to the angular momentum present in said body with a phase with respect to the nutation motion which tends to decrease the amplitude of the nutation motion.

Abstract: Quick release mechanism for a sprinkler head includes a latch assembly for holding the valve in sealing engagement over an outlet orifice. The assembly comprises a generally U-shaped ejection plate pivotally mounted between the sprinkler head frame and valve in canted relation to the center line of the sprinkler head, and a thermal responsive element mounted between the sprinkler frame and valve-holding end of the ejection plate. The thermal responsive element contains a pellet of fusible alloy and a ceramic bearing slug and glass ball to hold the element between the ejection plate and sprinkler head frame in order to optimize the response time. The whole pellet housing with its heat fins is effectively insulated from the rest of the latch assembly by the glass ball and an insulator sleeve at its extremities. When the alloy melts, the ceramic slug and glass ball drop downwardly, destabilizing the latch assembly and thereby permitting fluid pressure to blow the seal at the outlet orifice.

Abstract: A single file apparatus is provided for highly etched containers wherein a mass of containers is separated into two single file rows, the single file rows are merged into nesting relationship and the nested rows of containers separated and further merged into single file. The mass of containers are separated into separate rows along each side of an air conveyor having an imperforate cover forming a high pressure area between the rows. The differential pressure in this high pressure area is lower at the upstream end than at the downstream end so that containers which move into this central area will recirculate upstream. The separated rows of containers are brought into an alignment zone and arranged in nested relationship and are merged into an equilateral triangular configuration with mutually touching side edges in a nesting section within the alignment zone.

Abstract: A nutation damping control for a dual-spin satellite is provided by tilting the axis of the rotor relative to the normal spin axis of the satellite and back a half nutation period later. The tilting is in the direction of the angular momentum vector component that is transverse to the rotor's spin axis.

Abstract: A wing having a cantilevered support for changing the camber thereof is attached at a stressed wing portion so as to be pivotable about an axis rigidly attached to the wing. Sliding carriages having gear wheels are attached in a guide channel in the wing cantilevered support and a toothed rack attached at a landing flap is guided between the gear wheels so that the distance traveled by the sliding carriage can be selected to be different from the distance through which the flap travels during lowering or extension thereof. Actuation of the landing flap occurs by means of a hinged crank and a connecting rod which drives the sliding carriage and, in order to cover a gap between the flap and a spoiler which is provided, the spoiler is designed with a flexible configuration.

Abstract: A non-rigid, gas inflatable airfoil having a bulbous inflatable forward body and three spaced-apart rearwardly extending inflatable tails. The tails are attached to the rearward portion of the body and form with the body a single inflatable chamber. The central tail is yieldably biased into an upwardly inclined position, and a pair of sheets extend between the tails. The airfoil has a generally delta shape and provides a positive lift when exposed to wind. The airfoil is connected to a single tie down line by a single attachment member and swivel attached to a central portion of the underside of the body. The body and tails have sufficient interior gas containing volume that when filled with a lighter-than-air gas will offset the weight of the airfoil. The bulbous body contains enough lighter-than-air gas that the airfoil assumes a vertical orientation with the body above the tail when in the water or in the air without wind.

Abstract: A nesting table is provided which receives containers en masse from a mass air conveyor at an upstream end and discharges the containers onto a deadplate in three rows in contiguous equilateral configuration. In one embodiment, a high air pressure zone is provided along the nesting table by means of a cover extending from one side across the table to a point spaced at least one container diameter from the opposite side so that the containers entering the nesting table form two longitudinal rows on opposite sides and fill in between with a third row which nests with the row of containers which is not under the cover. A kicker plate is provided downstream of the cover to move the three formed rows of containers into nesting contiguous equilateral configuration for movement onto a deadplate. In a second embodiment, the cover is spaced at least two container diameters from the opposite edge and tapered side guides converge the three rows of containers.

Abstract: A continuous main strap (10) has a front H-shaped configuration and a rear X-shaped configuration. Strap (10) extends from one side of the waist diagonally up and across the back, down the front, across and under the buttocks, up the front, and diagonally down and across the back to the opposite side of the waist. A chest strap (30) completely encircles the chest and forms the horizontal portion of the "H". An integral thigh strap and lap belt (20) is attached to the buttocks portion (16) of strap (10) and extends upwardly and laterally outwardly to side waist fittings (56) on vertical front webs (14) of strap (10), through fittings (56), and inwardly to an adjustable connector (26). Each fitting (56) has a cam lock snubber (66) for releasably securing strap (20) against movement relative to fitting (56).

Abstract: A hydraulic control cylinder (64) is used to swing the upper part (14) of a two part wheel strut (14, 16) about an axis of rotation (18) established at the upper end of the upper strut part (14) and at an upper central location within a stowage compartment (10). A folding drag brace assembly (102) is connected between the strut (16) and a lower rear portion of the stowage compartment (10). During use of the control cylinder (64) for swinging the upper strut part (14) rearwardly and upwardly, the drag brace (102) folds automatically in the manner of a pantographic device, and functions to fold the lower strut part (16) up against the upper strut part (14) within the stowage compartment (10). A mechanism is provided for rotating the wheel assembly (30) W, relative to the lower strut part (16), for the purpose of properly positioning the wheel assembly (30) W for movement into the stowage compartment (10).

Abstract: An inward/outward movable plug-type aircraft passenger door (50) including: (i) a hinge assembly (56) and programming control mechanism (100, 114, 116 and 105, 114, 119) therefor; (ii) a latch/unlatch mechanism (58, 70, 82, 88, 89, 90, 91, 92, 94 and 95) therefor; (iii) a pressure lock gate (69) and actuating mechanism (58, 75, 76, 78, 79, 80, 81, 82 and 84) therefor; and (iv), a deployable emergency evacuation system (59) and actuating linkage (60, 132, 134, 135, 136, 138, 139, 140, 141, 142 and 144); wherein the aircraft door (50) is of the type adapted to be translated between a first fully closed and latched position and a second fully opened position while being maintained essentially parallel to the plane containing the ingress/egress cutout opening (51) in the fuselage (52) at all intermediate door positions--i.e.

Abstract: An indexing mechanism for use with a deployment mechanism of a ram air turbine having front and rear linkages pivotally connected at one of their ends within the storage bay of an aircraft and their other ends pivotally connected to a housing for the ram air turbine, for moving the ram air turbine between a stowed and deployed position. The improved indexing mechanism includes a spring-loaded detent member coupled to the housing which engages a slot in the turbine hub preventing rotation of the turbine hub and blade when the ram air turbine is in the stowed position. Coupled to the rear linkage adjacent the pivot joint at the ram air turbine is a cam member which moves through an arc as the ram air turbine is deployed, said cam member engaging the spring-loaded detent member to release the turbine hub and blade as the ram air turbine nears the fully deployed position.

Abstract: A torpedo recovery unit positionable within a torpedo casing having an opening for receiving the unit. The unit includes a body with an interior cavity having an open end mountable within the torpedo casing with the open end at the torpedo casing opening. The body is rigidly supported within the torpedo casing. A non-rigid, gas-inflatable airfoil is foldable within the body cavity for deployment therefrom upon inflation. A bottle containing pressurized helium is rigidly and removably attached to the body. A release valve on the bottle releases the pressurized gas on depression. A valve member is rigidly attached to the body. A first end portion extends through the body end wall and projects into the body cavity and has an inflation needle mounted thereof for inflation of the airfoil. A valve member has a second end portion positioned outside of the body and operatively engaging the release valve when the bottle is attached to the body.

Abstract: This invention relates to a mechanism for automatically actuating a rescue device upon opening of a panel obturating an exit and bearing said rescue device, mechanism comprising a control bar connected to said rescue device and adapted, under the action of a voluntary actuating member, to be rendered fast either with said panel or with the periphery of said exit, with the result that opening of said panel does not bring about, or brings about, respectively, actuation of said rescue device via said control bar. According to the invention, this mechanism is characterized in that said control bar is fast in displacement with a mobile system controlled by said voluntary actuating member in order to subject said bar to a movement of translation parallel to itself, of direction at least substantially at right angles to said panel. The invention is more particularly applicable to the automatic control of escape slides, slide/rafts or the like in the event of an emergency.

Abstract: The invention concerns a steered aerostatic balloon and in particular the creation of balloons of large volumes, which are free (airships, space balloons) or captive (material loading or unloading balloons). This balloon has an outer envelope (1) containing air, an interpolar connector (11) connecting the lower pole (2) and the upper pole (3) of this envelope, a grid of longitudinal reinforcements (8) connected to the poles (2) and (3), a grid of circumferential reinforcements (8) connected to the poles (2) and (3), a grid of circumferential reinforcements (7), at least one inside envelope (12) within the first envelope and containing helium, this latter envelope during inflation coming to rest against the outer envelope and being provided with poles fixed on the interpolar connector (11), and lastly air intake means and air evacuation means to and from the outer envelope.