Abstract: A helicopter equipped with a reciprocating piston internal combustion engine in which an override clutch is arranged in a drive connection between the internal combustion engine and a rotor drive, is equipped with separate first and second electric motor starter devices (screw-push starters). A starter operation takes place in two phases whereby in a first phase initially the rotor drive is brought to a rotor synchronous rotational speed syn by means of the first starter device and in a second phase the internal combustion engine is started by means of the second starter device. When the internal combustion engine exceeds the idling rotational speed nl, the override clutch establishes the power-flow connection between the internal combustion engine and the rotor drive. Both phases can be carried out manually as also by a partly automatic or fully automatic control system on the basis of key depression.

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: A drive arrangement for an aircraft with a propeller, especially a thrust propeller arranged in the rear fuselage of an aircraft frame which is connected with a drive unit. The drive unit is connected with a longitudinally installed tubular support member supportingly receiving a central shaft. The tubular support member as well as the drive unit are supported on the side of the fuselage by way of at least three elastic bearing supports. One bearing support is provided at the aircraft rear end of the tubular support member and the two other bearing supports are provided within the area of the drive unit.

Abstract: A method and apparatus for extending the load support surface of an aircraft cargo pallet (8) to make use of those side areas (6) of the cargo hold located above the curved side walls of the aircraft. Triangular section load support members (9) formed from corrugated cardboard are provided on either side of the pallet, held in place by tensioning straps (19) extending either through the layers of cargo (17, 20) or inwardly and downwardly to the pallet edges. The upper surfaces of the load support members (9) form an extended load support surface (11) for the upper layers of cargo (21). extending the cargo area out toward the curved sides of the hold.

Abstract: The invention is a small flap like device (18) for attachment to the trailing edge (14) of an aircraft wing (10) which improves the coefficient of lift and reduces the coefficient of drag providing an overall increase in fuel economy. The flap (18) is a flat plate-like member having a length (19) of between 0.5% to 1.5% of the chord of the airfoil and at a downward angle (21) to the chord of between 5.degree. and 25.degree..

Abstract: A retainer for an aircraft rudder for holding stable such rudder during storage but which retainer will automatically remove itselt from the airplane should the airplane be taxied from its storage position without the retainer first being removed from the rudder.

Abstract: A parachute deployment actuator incorporating an aneroid with a relatively long strike results in a significant diminution in the degree of precision with which the associated parts have to be made. A spring is provided externally of the aneroid in such relationship as to augment the natural spring force tending to expand the aneroid, such spring operating not only to keep the aneroid off its internal stop at sea level but also to cause the overall system to have a desired spring rate. A variable lever system inter-relates a preprinted scale and associated altitude cam with the aneroid in such relationship that the parachute actuator will release the chute very near a pre-set altitude.

Abstract: A multi-media craft particularly designed and constructed for efficient and economical utilization on land, water and in the air and comprising a light weight body constructed in modular form for economy and power by a removable lightweight engine of the motorcycle type for fuel efficiency and ease of maintenance. The craft is provided with forward and rearward sections constructed in a manner for variable in-flight or in-use alteration or molding thereof for achieving the optimum planar or contour design for the craft as required during variable fluid conditions when airborne, thus providing efficient and safe flying operation for either an unskilled or skilled operator.

Abstract: A towable gliding flexible wing craft for hauling a payload including a passive control means for responding to deviations from level flight. The gliding wing craft comprises a gliding flexible wing, spreader bar, support means for securing said gliding flexible wing to said spreader bar, a bridled tow line secured to said spreader bar for towing said gliding craft, means for securing said payload to said spreader bar and control means for causing wing tip lift or control dragulation of said wing. The control means is capable of passively responding in an opposing manner to deviations from level flight resulting in substantially level flight.

Abstract: The invention improve hot air balloons of the type using heavy duty propane burners producing large unconfined flames by manually controlled intermittent short combustion periods,--the type used for the sustained flight and transport of one or more passengers. The improvements comprise increased lift and rate of lift, fuel economy, safety of components and passengers, envelope life, and elimination of scorching and near-scorching of the envelope and skirt, reduced cumulative deterioration of the envelope; these improvements are accomplished by the elimination of the hiterto unrecognized large loss of radiant energy from the flame which has passed through the transparent gas and translucent portions of the envelope (thin, light colored) and being lost without having heated the interior gases,--by means of opaque shields of metal and/or fabric suspended between the flame and the envelope to intercept the radiant energy, convert it to heat energy and transfer it to the contiguous gases.

Abstract: An aircraft flight control surface actuator that prevents against overtravel is provided with a lock which includes a pin (76) that is urged by spring (b 74) toward the wall (68) that is part of control gear (56) which travels along the axis of a threaded shaft (42) in response to rotation of main shaft (16). An aperture (70) in the wall (68) is aligned with pin (76) only at a neutral position of the flight control surface (12). Lever (80) depresses pin (76) against the force of spring (74) only so long as hydraulic system pressure for the actuator is supplied to cylinder (84).

Abstract: A reefing system comprising an annular flexible membrane having a centrally located vent opening and a plurality of guides symmetrically spaced around the periphery of the membrane. The reefing system retards or slows opening of the canopy of a parachute in order to reduce the shock normally encountered with parachutes.

Abstract: The invention relates to a contoured wing intended to serve as a airfoil or a blade. This wing comprises a longitudinal stringer (3), a plurality of juxtaposed wing sectors (1, 2), each articulated about the stringer, a series of cranks (7), each crank associated with a sector in such a manner as to fix the angular position thereof about the stringer, and a control device (10) for the cranks, able to cause their pivoting. The wing according to the invention permits control of the angle, continuously and progressively variable along the contour. It may particularly be applied for use in beating wing aircraft.

Abstract: A lift enhancing system for an aircraft having wings and a deflectable airfoil attached to the trailing edge of the wing which includes ejecting nozzles attached to and movable with each deflectable airfoil to eject gas spanwise across the surface of the deflectable airfoil and thereby enhance the lift of the wing and deflectable airfoil.

Abstract: A special contour near the trailing edge of an airfoil which improves the airfoil effectiveness. The contour is a combination of a blunt airfoil base, a local region of high surface curvature, typically on the airfoil lower surface, and upper surface and lower surface trailing edge slopes that diverge from each other.

Abstract: The autonomous onboard device for loading a cargo-aircraft having a lateral door comprises hoisting means (10) movable between the exterior and the interior of the fuselage (F) of the aircraft along carrier and guide means (3,4,5), which comprise transverse rails (3) inside the fuselage at the level of the upper part of the lateral opening (1) and two arms (4) provided with rails (5) movable between an extended position, in which they are in the extension of the rails (3) outside the fuselage, and a retracted position in which they are withdrawn into the fuselage. This device is light weight and of small size.

Abstract: An aircraft having paired aerofoils 12, 14 and 24, 26, the wing tips 16 and 18 being joined in the same plane one behind the other. The trailing edge of the forward wings and the leading edge of the rearward wings being substantially coincidental in plan view at the wing tip. The minimum angle between the wings 12 and 24 is 4 degrees at the tips of the wing. The substantial part of the forward wings is higher than the rearward wings.

Abstract: An assembly comprises drive key wearplates mounted in pairs to longitudinal side surfaces of each of a plurality of wheel key bosses and retaining members are fastened transversely across the top of a boss to engage both wearplates of the pair. A heatshield is positioned within the wheel bore between adjacent wheel key bosses and its opposite lateral edges engage respective wearplates in a manner such that it may not move either axially or radially within the bore.

Abstract: The present invention relates to a new and unique structure in a collapsible decelerator for aerial bodies launched from a high velocity vehicle and designed to provide a high drag stabilizer capable of withstanding release in air stream velocities from subsonic to supersonic. The decelerator preferably includes a hollow inflatable star, the outermost points of which have hooded valve openings through which regulated airflow enters and inflates the star to decelerate the body to which it is attached. The new and unique capability comprises an angular offset of each air scoop to create desired rotational speed in the selected direction.The amount of angular offset and protrusion into the air stream controls the magnitude of spin rate, the direction of angular offset controls the direction of spin.

Abstract: Axial motion of the wheel assembly of a flat-spring undercarriage for vertical-lift aircraft is provided to permit proper deflection of the flat spring so as to effectively cushion the touchdown of such an aircraft from a hover.