Abstract: An oil tank for an aircraft mounted engine compensates for differences in oil capacity occasioned when the oil tank in each engine mounted under the wing is oriented with respect to the wing's dihedral angle and the angle of the engine which is normal to the wing. The tank includes a first portion for receiving the oil and integral expansion portion where the oil tank is below the right wing dihedral and the expansion is above the left wing dihedral.

Abstract: An aerofoil body, for example a "delta" wing aircraft, in which strip-form devices project rearwards from the trailing edge of the wing and serve to improve the lift-to-drag ratio of the body, in some conditions of flight at least, by modifying the formation of the trailing edge vortex to allow the axes of the primary vortex sheets to lie closer to the fore-and-aft centerline of the body than would otherwise be the case. When the strips are basically flat in shape, the strips may project straight backwards from the trailing edge or may be angled in various ways. The use of twisted strips is also described.

Abstract: A guiding system of the movable fairing of a turbojet engine thrust reverser system comprising two guide pieces mounted on an upper frame fixed to a mast and pieces to be guided attached to the movable fairing. The guide pieces are provided with a groove of a circular cross section and the piece to be guided is a cylindrical body having, on a generatrix and in a radial plane, a flange, the end of which has means to fasten it to a fitting on the movable fairing.

Abstract: A force control member assembly 1 comprises a force control member unit 2 carried by an intermediate member 3, the intermediate member 3 itself being attached to a fixed bracket 4 by pivot means 5 allowing resilient movement of the intermediate member 3 with respect to the fixed bracket 4 about pitch and roll axes as shown at 6. The force control member unit 2 includes a force control member and force transducer means associated therewith to generate force control signals related to control forces applied to the force control member. In use, when a control force is applied to the control member, a force control signal will be generated simultaneously with a significant displacement of the intermediate member with respect to the fixed member. The intermediate member will return to a median position on removal of a control force; this imparts a `feel` characteristic to the assembly.

Abstract: A swivel-mounted trim element of a predetermined configuration for use with aircraft for the purpose of providing additional control in flight. The trim element is mounted immediately to the rear of a channel-shaped stabilizer mounted externally or molded into the fuselage of an aircraft and is especially suited for small aircraft, particularly those having V-surface tail assemblies. The trim element configuration is generally right-angled with the base portion being additionally formed to have a downwardly-canted portion at the leading edge and an inwardly-canted portion at the trailing edge. In operation, the trim element provides two-axis rudder trim about both the pitch and yaw axis.

Abstract: A retractable aircraft step module comprises a streamlined fairing having a recess for receiving a retractable step member which is connected to the fairing by spaced apart pivot links which together with the step member and the body member form a four bar linkage. The linkage includes a deflectable pivot connection between one of the links and the step member which provides a biasing force to maintain the step member in the retracted position. The deflectable pivot connection is provided by a pivot beam mounted on the step member and including a counterdeflection adjustment for preselecting the maximum biasing force. The step member and the fairing are adapted to mount on the exterior of an aircraft fuselage and are preferably constructed of reinforced plastic.

Abstract: A landing mat for compacted terrain is formed by assembling a multiplicity of mat elements in contiguous relationship. Each of these elements has a rectangular plan configuration and is formed along its longitudinal edges with downwardly bent flanges, and between these flanges, with flattened corrugations forming longitudinal ribs perpendicular to the planar upper surface of the element. Stabilizing plates can extend transversely to the ribs and flanges and can have upwardly open slots snugly receiving the ribs. Clips bridging contiguous edges of adjoining elements are fitted into elongated windows spaced inwardly of these edges to hold the elements together and an edge member, likewise having a flattened-corrugation rib, is fixed along one edge of the mat and has downwardly turned tongues fitted into the window of the elements along the latter edge.

Abstract: A hollow reinforced concrete sphere can be used as a container for transporting compressed gas, such as natural gas. Such containers can be interconnected and towed from one place to another by an ocean-going tugboat. Each container is formed with three band-like groups of reinforcing rings. Each group has its reinforcing rings disposed at right angles to the reinforcing rings in the other groups. The inner and outer surfaces of the container walls can be covered with a desired coating. In constructing the containers, they can be built at the water's edge and then rolled into the water.

Abstract: A steering apparatus for an outboard jet engine utilizes a channel or conduit along the underside of a boat hull in combination with a channel or conduit extension member to guide water to the inlet port of the jet outboard propulsion apparatus, the bottom lip of the inlet port being disposed proximate the extended bottom surface of the underside of the boat hull with the top lip or rim of the inlet port being disposed proximate the extended top surface of the channel of conduit along the hull to permit propulsion and steering of the boat while the boat hull is planing along the surface of water only inches or centimeters above the bed of the lake, river or ocean.

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.

Abstract: A flexible helicopter rotor includes a vertical rotor axle, a mechanism for rotating the vertical rotor axle in a first rotational direction, and a plurality of segmented flexible airfoils secured to and extending radially from the vertical rotor axle, each segment of each airfoil forming a billowing, canopy-shaped surface as the vertical rotor axle is rotated. Each airfoil includes a cross spar extending radially from the vertical rotor axle and in turn supporting first and second leading edge spars and first and second keel spars. The forward ends of the leading edge spars and keel spars are joined to form an apex of the airfoil at a point ahead of the cross spar. A flexible membrane is secured to the first and second leading edge spars and to the first and second keel spars and is divided thereby to form the segmented flexible airfoil.

Abstract: A flotation device for supporting a person in water comprises an elongate tubular frame including at least one body-support member, and front and rear float assemblies mounted on the frame. The rear float assembly comprises two float elements spaced apart transversely of the elongate frame, and the float elements are so disposed that, when the device is floating in the water, the body-support member is below water level, so that a person using the device is partly in the water.

Abstract: A tracked, amphibious vehicle with track securement and guide means for the track to prevent "track throw" or loss. The vehicle includes two spaced, parallel pontoons joined by a centrally located operator's platform structure, with each pontoon having a moveable track for propulsion, with the track supported on its pontoon by fore and aft sprocket wheel sets and a series of larger bogie wheels at its bottom and smaller guide wheels at its top. Each track comprises a parallel set of rubber, continuous, endless belts joined together by a series of laterally disposed cleats with drive lugs, which lugs are engaged by the teeth of the sprocket wheels. For track securement in a first embodiment (FIG. 5) every fifth cleat includes an inwardly projecting, polyethylene T-hanger retainer which matingly fits and rides in a beam guide attached to the bottom of the pontoon and extends from the initial bottom bogie wheel to the entry of the aft, drive sprocket. In a record embodiment (note FIG.

Abstract: The subject of the invention is a suspension device for a helicopter, intended for reducing the vibrations caused by its rotor. The main transmission box of the rotor is supported at the top by a set of oblique articulated bars and is bolted at its bottom to a diaphragm made of thin sheet metal, which can be deformed by bending, but not by shearing in its plane. Flexible arms arranged radially and supported by fixed mountings are articulated to the foot of the oblique bars and to the bottom of the transmission box; they each carry, at the end of a lever, a swinging weight acting by the effect of inertia.

Abstract: A slat assembly is mounted upon the leading edge of an aircraft wing, and responds automatically to changes in air speed or in the angle of attack of the wing, to increase lift at lower air speeds, and to reduce the stalling speed of the wing. A capability is induced in the aircraft for landing and taking off in short distances. For an aircraft of given size and power, also, there is offered an added safety factor in that the aircraft is permitted to land at slower landing speeds than have heretofore been possible. For the purpose of accomplishing these results, the automatic leading edge slat utilizes a base plate projecting from the leading edge of the aircraft wing, and supporting a slat having airfoil characteristics forwardly of the leading edge of the wing.

Abstract: An exhaust system for an outboard engine that improves exhaust efficiency and silencing at low speeds. The low speed exhaust gases are delivered to the atmosphere through a predetermined water level that is maintained in a separate water reservoir.

Abstract: A mooring device for use, particularly in the mooring of an aircraft such as a helicopter on the deck of a ship includes a grid having an upper surface adapted for engagement by a harpoon carried by the aircraft. The grid comprises a plurality of substantially identical elements and retaining means secured to the deck and adapted to retain the elements in juxtaposed relationship. In one embodiment the elements are generally rectangular in plan and have an upper surface provided with both full and half apertures arranged so that when in said juxtaposed relationship, the elements combine to provide a generally continuous apertured upper surface.

Abstract: A radar chaff spreading device for mounting on an airplane equipment support beam. The device includes attachment means from which additional equipment, such as a missile, can be suspended. The chaff spreading device further includes coupling means for receiving power and control signals from the airplane and for transmitting control signals to the additional equipment.

Abstract: A design system for aircraft that allows wings of various different planforms to be mounted interchangeably on a common fuselage. Each of the wings has wing semi-spans joined by a center section torque box that mounts the wing in a cut-out in the aircraft fuselage. The torque box has a quadrilateral structure including front and rear main center section spars. These center section spars have their ends connected to the front and rear main spars of the semi-spans to transmit wing loads into the fuselage. The length of the main center section spars are designed in accordance with the invention such that they can connect with the main spars of the wing semi-spans to position the quarter chord of the wing properly with respect to the center of gravity of the aircraft irrespective of the wing planform. Thus, aft-swept, forward-swept, or straight wings can be routinely interchanged on a common fuselage without effecting the positive static longitudinal stability of the aircraft.

Abstract: An improved crashworthy helicopter seat primarily for combat aircraft includes at least upper, intermediate and lower pairs of energy absorbers attached between the seat bucket and the frame of the aircraft and operable in both tension and compression. The energy absorbers comprise a plurality of telescoped tubes interfitted into one another and having coils of wire frictionally engaged between adjoining tubes such that energy is dissipated by motion of the tubes relative to one another through the plastic deformation of the coils of wire. The energy absorbers are adjustable to optimize safety parameters of occupants of the seat under a range of potential crash conditions including the most probable crash condition, for occupants having a substantial range of weight and size.