Abstract: A telescopic airfoil comprising a plurality of short wing sections, each consisting of skin and rib, with tubular spar sections attached to the rib. Each spar section is adapted to telescope with respect to the next adjoining spar section toward the root end of the airfoil. Alternate spar sections are rotatable, and intermediate spar sections are held stationary, with the end portions of adjacent spar sections overlapping, and low-friction threads connecting the overlapping spar portions. The threads at opposite ends of each spar section are of opposite hand so that rotation of the rotatable spar sections causes the entire group to be drawn together into a housing at the root end of the wing. In this way, the wing span can be reduced to less than 30% of the full span, while during extension and retraction, the spars retain their full load-carrying capability.

Abstract: Modules (30) include lateral bearing beams (32) for distributing cargo loads over a cargo compartment floor (4). Roller trays (34, 34', 34") are secured to and extend longitudinally between the beams (32). A tie-down support beam (38) is secured to and extends longitudinally between outboard portions of adjacent bearing beams (32). The support beam (38) is anchored to a rail (12) mounted in the floor (4). A side guide (40) is attached to of the bearing beams (32) and carries vertical restraint members (46) and a longitudinal restraint latch (48). Adjacent modules (30) are connected by slip joints (68). A cargo tray (80) has sloping sides (86) to conform to curving cargo compartment sidewalls (6). Slots (102) on the sides (86) engage the restraint members (46). The tray (80) has an outer shell (82) and a corrugated inner shell (90) with ridges which form support surfaces ( 98) coplanar with a peripheral horizontal lip (106).

Abstract: The shock absorbing jack of the invention includes essentially a rod in which a sliding piston defines an extension chamber and which itself slides in a body by means of a piston defining a retraction chamber, the body including a throttling device and, on the side opposite the rod, two high and low pressure gas chambers, these chambers being separated by a membrane bearing, at rest, on a support with hemispherical perforated bottom.

Abstract: A nozzle for a gas turbine engine having a first fixed petal 44 and a second movable petal 46 which is pivotally mounted at a point intermediate its leading edge 46(a) and its trailing edge 46(b). Actuation means 48 are provided to move the nozzle between a first and a second position. In the petals first position, its leading edge 46(a) is positioned forward of and slightly radially inward of the trailing edge 50 of the exhaust duct 52, such that a small ejector gap 54 is provided therebetween and the trailing edge 46(b) approaches the trailing edge 44(b) of the fixed petal, such that the gap therebetween defines the exit area of the nozzle 36. In the petals second position (shown dotted), its leading edge 46(a) is moved radially inwards of its trailing edge 46(b) such that the exit area of the nozzle is defined by the area between the trailing edge 50 of the exhaust duct 52 on the second petal side and the trailing edge of the first petal 44(b).

Abstract: A method for controlling an aircraft to prevent high G-caused pilot unconsciousness. Data defining a state space of acceleration, rate of change of acceleration and duration of acceleration at maximum acceleration within which an aircraft may be operated without causing pilot unconsciousness is provided to an aircraft intelligent flight control system. The flight control system continuously monitors the past and present state of the aircraft and compares to the surface boundaries of the defined safe state space, Whenever the aircraft exceeds those boundaries, the flight control system intervenes to unload the aircraft to within those boundaries. Additional data and measurements may be added to define an n-dimensional state space. Another embodiment unloads the aircraft to a baseline acceleration. A simplified embodiment is described which compares current acceleration to a preselected value of acceleration.

Abstract: A strut for mounting an engine and isolating the vibration of the engine from the framework of an aircraft to which it is attached. An engine mounting strut (32) includes a forward spar (40), which extends outwardly from a rib (34) of an aircraft (20). An aft spar (62) similarly extends outward from a rib (38) and is pivotally connected to a box beam (42) in a vibration isolation mount (78). The pivotal axis of mount (78) is generally aligned with the longitudinal axis of the box beam. A vibration isolation arm (44) extends from a pivotal connection (82) having an axis generally orthogonal to the longitudinal axis of the box beam and is connected to the forward spar at two spaced-apart vibration isolation mounts (46 and 84). The spars are enclosed with an aerodynamic skin (56) forming a torque box 48, to which are attached forward and aft fairings (58).

Abstract: A safety chamber of the telescopic type usable for an airplane includes a plurality of wall segments, granular cushioning materials and a parachute. As long as it is not in use, the wall segments are accommodated in a contracted state in the space on the ceiling of the airplace. In the event of an occurrence of emergency the wall segments are lowered one after another to constitute a chamber in which a single seat assembly is incased together with passengers sitting thereon. When the lowermost wall segment reaches the floor of the airplace, a plurality of hooks around the lower edge thereof are engaged with recessed parts on the bottom of the seat assembly and at the same time the cushioning materials fall down from the ceiling while expanding by themselves whereby the hollow space in the expanded chamber surrounding the passengers is filled with cushioning materials for the purpose of preventing the passengers from the influence of shocks.

Abstract: A device for retracting a separable component of an object on separation of the object from a launcher, the device comprising a housing attached to the launcher, a power spring in the housing for the component on separation of the object from the launcher, a shaft connected to one end of the power spring for winding the power spring during loading of the object on the launcher, a lock for automatically fixing the power spring in a predetermined wound position, an annular flange structure connected to the shaft for automatically preventing over winding of the power spring, and a cam device responsive to separation of the object from the launcher for releasing the lock.

Abstract: A hand-operated control system for aircraft comprises a push-pull cable operatively connected between a hand-operated actuator and an orientation means that controls the orientation of the aircraft during flight. The actuator is mounted on an existing hand-operated control in the cockpit of the aircraft with sufficient slack in the cable to permit independent operation of the control cable and existing control. The control system provides a redundant control system for pedal-operated controls, thereby allowing wounded pilots, paraplegics, and others to control pedal functions by hand manipulation of an actuator on an already existing hand-operated control.

Abstract: A plastic shield for a connector link for connecting parachute shroud lines and a riser. The protector shield has a first member with channels which receive a portion of the connector link and a second member which is complementary with the first member and has channels which receive a portion of the connector link. The first and second members of the protector shield are attached by a set screw in surrounding relationship to a portion of the connector link to minimize contact between the connector link and a slider grommet on the shroud lines when the parachute slider and slider grommets located thereon move downwardly along the shroud lines so that the surface of the slider grommet is not nicked by contact with the connector link.

Abstract: Helium inflatable emergency locator balloon having a longitudinal body and side wings defining horizontally a triangular, bilaterally symmetrical tetralobate monochamber having a forward lobate nose, a rearward lobate hind section and flanking rearward lobate wings, the latter three lobate portions being in side by side spaced apart and unconnected relation to each other and the hind section end extending rearwardly slightly beyond the wind ends, and in inflated condition each of the body and wings defining in longitudinal cross section a bilaterally symmetrical convex profile having a slightly rounded upper side and underside, a small rounded leading edge and an acutely pointed trailing edge, and a respective tail of streamer strips attached to each of the hind section and wing ends, such strips preferably constituting tuned radar reflective dipole strips, and optionally alternatively similar dipole strips being individually loosely disposed within the balloon, and a gas supply device for inflating the ballo

Abstract: A nacelle wing combination wherein said nacelle can be mounted below the wing and positioned closely to the wing, without creating excessive nacelle induced drag. The wing is contoured so that peak low pressures below the wing occur near the mid chordwise location at the lower surface of the wing. Thus, the channeling of air passing over the nacelle and under the leading edge of the wing does not create supersonic velocities which would create excessive drag.

Abstract: A system for automatically controlling the buoyancy of a lighter-than-air craft by condensing water ballast from engine exhaust gases.

Abstract: An airfoil has a plurality of spaced apart, U-shaped troughs in either or both its suction or pressure surface in the trailing edge region. Each trough extends in a direction generally parallel to the bulk fluid flow in its vicinity near the airfoil surface and has an outlet at the trailing edge. The troughs increase in depth from their inlets toward their outlets, the maximum depth being no more than half the trailing edge thickness. The troughs are spaced apart, sized and configured to flow full over their entire length and to cause fluid to flow into the space immediately behind the trailing edge, thereby reducing base drag.

Abstract: A kite comprising at least two bags into which the wind is blowing through air openings in the front end of the bags, and which are joined to each other by a horizontal seam. The shroud line is attached directly to the seam or to a keel which is attached to said longitudinal seam in the middle of the kite. The air openings are diminished by pleats or the like along the edges of the openings. The openings can be closed after the filling with air or gas in which case the kite is flying like a balloon.

Abstract: A fluid mount particularly suited for mounting an engine in an aircraft. The mount includes a frame which is fastened to the engine and a support movably mounted in the frame and adapted to receive a wing pylon stub shaft. Opposed liquid-filled chambers are provided on opposite sides of the stub shaft support and are fluidly interconnected by an elongate tube. An auxiliary chamber is provided on the frame adjacent to the upper liquid chamber and is divided internally into a gas-filled portion and a liquid-filled portion which is in communication with the upper liquid chamber via an orifice. The auxiliary chamber accommodates changes in liquid volume without adversely affecting either the static or dynamic performance of the mount.

Abstract: A cyclic control stick of the type used in helicopters for reducing the safety hazards associated with such a mechanism in the event of a crewman being thrown violently into contact with the cyclic control stick resulting from a crash or the like. The cyclic control stick is configured to break away upon the exertion of an impact force which exceeds a predetermined value and/or is exerted for more than a momentary time duration. The cyclic control stick is also configured to be adjustable so as to locate the grip thereof as far away from the crewman as possible for safety reasons without comprising the comfort of the crewman or the use of the control stick, and a crushable pad is provided on the top of the grip for impact energy absorbing purposes.

Abstract: The invention is directed to a thrust vector control for aircraft with one or more jet engines whose thrust nozzles have an adjustable size exist cross-section, each of the jet engines having a ring rudder axially spaced behind the engine and movable about at least one pivot axis extending substantially perpendicular to the engine's longitudinal axis. A substantially planar rudder plate is secured diagonally in the inside cross-section of the ring rudder for each plane defined by each pivot axis and the longitudinal axis of the engine. The rudder plate or plates each consist of a material which is stable at high temperatures without supplementary cooling and which is mechanically loadable, and the connection between the rudder plate or plates and the ring rudder each include a layer of elastic and thermo-insulating material.

Abstract: A helicopter having a body and a tail boom connected, at the rear end, to an integral tail unit, and on which each of the vertical sections formed through the body and the tail boom presents a profile having a substantially ogival upper portion becoming gradually more pointed the closer the vertical section is to the tail unit, and a substantially flat lower portion blending, to form a substantially sharp edge, with the opposite ends of the upper portion; the connections between the upper and lower portions of the vertical sections defining two continuous edges extending from the front end of the body to the rear end of the tail boom, and intersecting a lower fin on the tail unit, the surface of which is a continuous arrow-shaped wing surface.

Abstract: An airfoil having a trailing edge flap assembly comprising a flap member having a track mounted thereto. The track member is operatively connected to a slide-block which is in turn mounted to stationary structure. High Fowler motion is accomplished with this arrangement. In another embodiment the flap is additionally provided with a foreflap. In further embodiments, the flap assembly is provided additionally with aft flaps.