Abstract: A system for controlling the low altitude extraction of cargo from aircraft having a two part force transfer link assembly connected between drogue parachute and a main parachute. The link assembly is held in a tow-plate link release mechanism. The link assembly can be released by an electrical command signal from the aircraft cockpit or manually by a mechanical control system near the compartment bulkhead. The mechanical control includes a push-pull cable which operates the link release mechanism or which operates only a part of the link assembly to jettison the drogue parachute.

Abstract: An adjustable litter support assembly includes fittings on each stanchion to engage conventional hold-down fixtures on the floor of an aircraft. The stanchions are further supported by interconnectable connecting links carried near the top of each stanchion. Connecting straps also extend from near the top of each stanchion to a floor fitting near the bottom of the other stanchion of each pair. Litter support arms are adjustably connected to each stanchion and carry locking straps for detachably holding a litter thereon.

Abstract: An aircraft console provided with a pair of opposed shell housing members which matingly engage to provide an aircraft console outside wall housing. Each of the shell housing members provided with outwardly extending floor-engaging flange portions along the lower perimeter thereof. The floor-engaging flange portions cooperate to form a floor-engaging stabilizing support flange along the bottom perimeter of the assembled aircraft console. A plurality of internal partition panels and compartment floor panels provided which are selectively oriented to form a plurality of compartments within the aircraft console when fixedly positioned intermediate and in fixed engagement with the shell housing members. Transversely oriented connector floor-engaging anchor panels provided transversely across the bottom of the aircraft console so as to matingly engage the stabilizing support flange.

Abstract: A powdered material hopper or container is mounted in an airplane with a downwardly facing discharge opening positioned immediately above a centrifugal material discharge wheel driven by a hydraulic motor positioned in the outer end of a pivotal support in the form of a pivotal hollow housing. The pivotal hollow housing can be pivoted between a first position in which the centrifugal material discharge wheel is adjacently facing the discharge opening of the container and a second position remote therefrom for permitting a rapid emergency dumping of all material from the container. Movement of the pivotal support means is effected by a hydraulic cylinder connected to the pivotal support means and a lug extending from the lower end of the container which also provides pivotal support for the pivotal support means.

Abstract: A mechanism for capturing and releasing a spinning object comprises an adaptor housing which has a passive turntable mounted thereon and a braking clamp which is carried by a suitable support structure. The passive turntable is mounted on the adaptor so as to be free to rotate about the axis of rotation of the spinning object. The braking clamp initially engages the passive turntable and thereafter applies a braking torque to the adaptor housing.

Abstract: An actuation system for rotating a control surface mounted on an aircraft airfoil, the control surface being rotatable about a first axis at an acute angle to the longitudinal axis of the aircraft is disclosed. The invention comprises a first crank having a first end and a second end pivotally mounted to the airfoil and rotatable about a spanwise second axis substantially perpendicular to the longitudinal axis of the aircraft. A second crank is pivotally mounted at its first end to the first crank and is rotatable about a third axis which is substantially perpendicular to the second axis. The second end of the second crank is pivotally mounted to the control surface. The second end of the second crank is rotatable about a fourth axis substantially perpendicular to the second and third axes. An actuator, substantially aligned with the longitudinal axis of the aircraft, is coupled to the airfoil and to the first end of the first crank.

Abstract: An aircraft wing and flap arrangement comprises a fixed wing (1) a flap (2) pivoted at (3) to the fixed wing and a variable camber upper surface member (6) anchored to the fixed wing and resiliently biased toward the flap at all times; a cam track (9) secured to upper surface member (6) and associated cam track engaging member (10) on an arm (11) secured to the flap to control movement of the upper surface member so that on relatively small deflections of the flap (2) the upper surface of the wing is substantially continuous, while on relatively large downward deflections the upper surface is urged, by cam track engaging member (10), away from the flap (2) to open a slot (12); the arrangement may include a lower surface member (14) which is urged towards the upper surface membr (6) on relatively large downward deflections of the flap (2).

Abstract: Disclosed herein is a marine propulsion device comprising a propeller shaft supported in a lower unit against axial movement and for rotary movement relative to the lower unit and including an axial bore extending from one end of the shaft, which bore defines an annular wall including first and second axially spaced series of circumferentially spaced cylindrical apertures communicating with the bore and having radially extending axes, respective balls in each of the apertures, first and second axially spaced facing bevel gears mounted in the lower unit co-axially with the propeller shaft for rotation relative to lower unit and propeller shaft and against axial movement relative to the lower unit and the propeller shaft, which first and second bevel gears include respective axial bores having therein respective first and second series of circumferentially spaced sockets opening radially inwardly and located in axial alignment with the first and second series of apertures in the propeller shaft, and an actuator

Abstract: For exploring the high density high temperature atmosphere of a planet at a stabilized altitude, a buoyant assembly comprising an inflatable envelope is used. A container connectable with the envelope and containing a liquid selected to vaporize in the planet atmosphere to an extent which decreases above the stabilized altitude and increases under the stabilized altitude, is launched into the planet atmosphere with the envelope in folded condition.

Abstract: Device for carrying under aircraft multiple loads disposed at variable distances between centers, the modification of the distance between centers being obtained by rotating load supports about longitudinal axes by means of bearings provided in the frame structure of the carrier device. Each load support may be rigid with circular sets of teeth engaged by matching teeth formed on arms fulcrumed by means of eccentric pins on the frame structure and controlled for a same load support by cam device rigid with a common shaft.

Abstract: A removable secondary aircraft fuel tank enclosure is provided which comprises a pair of substantially flat panels supported within the aircraft fuselage beneath the center wing tank and joined to each other to form a drip pan having a shallow trough for collecting liquid seepage from the tank. A drain line communicates with the trough for discharging liquid collections overboard. An upright removal panel attached to the aircraft structure sealably joins the drip pan fore and aft and means adjacent the enclosure seal the sides of the drip pan against the aircraft structure. Sponge rubber provides a peripheral seal on the flat panels and a plurality of peripheral overcenter fasteners support the drip panel and seals it to the end panels and aircraft structure.

Abstract: A boat rope controller includes a framework comprising two substantially parallel support arms which are bolted to a mounting bracket secured to the rear transom of a power boat. A reel assembly including a gear is rotatably mounted near the center and between the two support arms and a guide pulley is rotatably mounted near the end of the support arms and aligned with the reel assembly. The gear of the reel assembly is selectively engaged by a ratchet control to allow rope to be fed-out from the reel over the guide pulley or to prevent rope from being fed-out from the reel. A service cover encloses the controller and a crank assembly is inserted through the service cover and one of the support arm to engage and manually rotate the reel assembly. A brake drum is attached to the reel assembly and a brake band is selectively actuated to engage the drum and stop the rotation of the reel assembly.

Abstract: The front bearing for a landing gear trunion is carried by a rear wing spar and the rear bearing is carried by a landing gear beam which is pivotly attached at its inner end to the body frame. A main attach pin pivotally connects the outer end of such beam to a pair of connector plates, one located on each side of the connection. A pair of shear pins connect the connector plates to a short cantilever beam which is connected to and projects inwardly from the rear wing spar, generally in line with the landing gear beam. One of the shear pins is positioned generally horizontally outwardly from the main attach pin. The second shear pin is positioned generally vertically below the main attach pin. Generally vertical overloads are carried by the lower shear pin load and such shear pin is designed to fracture in response to a load slightly below the vertical load reacting capability of the reaction structure.

Abstract: A technique for monitoring the ablation symmetry of a reentry vehicle by implanting a boundary layer trip material into the nose-tip surfaces of the re-entry vehicle's nose cone. The implantation material is characterized by a density that is usually greater and surface roughness that is greater than that which characterizes the material forming the main portion of the nose cone.

Abstract: An enclosure for the below deck storage of volatile or flammable fluids, in compressed gas tanks which is sealed from the vessel interior, but downwardly vented to the outside so that tank or cannister leaks find a preferred path of safe exhaust while the cannisters are conveniently stored within. The enclosure includes a sealed housing which is adapted to be mounted to a bulkhead in a vessel and which has an opening on one side thereof and a lid removable from the opening in the housing to gain access to the interior thereof. Means are provided for sealing the lid to the housing. The base of the interior of the housing is molded to conform to the shape of a lower end of one or more cannisters containing the pressurized fluid for support of the cannisters within the housing against motion caused by movement of the vessel. The lid is also molded to conform to the shape of the top of the cannisters for restraining further movement of the cannister.

Abstract: A kite made of sheet foam material with a hinged airfoil which is resiliently biassed closed, or flat, and constructed so that it is opened by the wind, the amount of opening depending on the strength of the wind; the preferred embodiment includes a keel where the connection between the keel and the airfoil is made by thrusting rods through holes in the keel and holes are reenforced with a bent stiffening member.

Abstract: A multi-purpose mono-element airfoil is disclosed for aerodynamic and hydrodynamic vehicles and devices. The multipurpose mono-element highlift airfoil when utilized in an aerodynamic application provides a combined no-moving-parts high lift and cruise airfoil which in conjunction with a plenum, upon pressure initiation, causes pressurized air to issue from a slot tangent to the airfoil surface and remains attached to the airfoil's shaped trailing edge, providing a controlled resultant force of thrust. Upon application to hydrodynamic vehicles, the multi-purpose mono-element airfoil is placed in the freestream and provides turning or pitching forces to the vehicle without any deflection of itself or any mechanical components.

Abstract: A device for engaging and disengaging a line comprising a pair of pivotal arms turnable to an upright position and to a horizontal position and supported at a location close to a line engaging bitt opposed to and a distance away from a line guiding member, a pressing traverse arm extending between the free ends of the pivotal arms, a disengaging traverse arm extending between intermediate portions of the pivotal arms for disengaging the line from the bitt, apparatus for turning the pivotal arms to the upright position and to the horizontal position, and a pressing bed positioned to oppose the pressing traverse arm when the pivotal arms are turned to the horizontal position, the disengaging traverse arm being positionable above the bitt when the pivotal arms are in the upright position, the traverse arms and the pivotal arms defining a space for inserting the line therethrough. The line can be engaged with and disengaged from the bitt or bollard easily and properly.

Abstract: A flying craft has a supporting element with an opening in it. A driving unit with a propeller drives air downwardly through the opening. Vanes mounted on the driving unit break up the circular component of the air velocity and also counteract the torque on the driving unit. The downwardly moving air is formed into a laminar air stream by a second set of vanes which are connected to the supporting element for rotation therewith. The pitch of the vanes can be adjusted. Adjustment of the pitch of the second set of vanes may cause the supporting element to rotate and give the craft a gyroscopic stability. The craft is tiltable for maneuvering purposes.

Abstract: In a method of and apparatus for damping nutation of a spinning spacecraft (10), spin axis attitude disturbances are substantially reduced by controlling at least one nutation damping gas thruster (18) to fire with non-uniform gas pulses. During the beginning of a nutation control sequence, the duration of successive gas pulses is gradually increased (up pulsed) from zero to a predetermined maximum duration. The duration of successive pulses is then maintained constant for a time period. Finally, at the end of the nutation control sequence, the duration of successive gas pulses is gradually reduced to zero (down pulsed). Up pulsing of the gas thruster (18) is initiated in response to a predetermined maximum nutation angle measured by an accelerometer (20). Down pulsing of the thruster (18) is initiated in response to a predetermined minimum nutation angle. The number of variable and constant duration gas pulses delivered by the thruster (18) depends upon the mass distribution of the spacecraft (10).