Abstract: A sea anchor is disclosed which comprises a generally cylindrical body of cloth or the like material open at the forward end. The opposite end is provided with a hem through which a rope or the like is passed to draw the opposite end more or less closed. Tow members are secured to the periphery of the sea anchor at the open end of the body, and a single control line is connected adjacent the opposite end of the body. Pulling on the control line independently of the tow members partially inverts or turns inside out the body of the sea anchor, thus reducing the maximum depth thereof, and greatly reducing the drag, thus to limit the anchoring effect, and to facilitate return of the sea anchor to a boat or the like.

Abstract: A crashworthy vehicle seat comprises a seat bucket member suspended by supporting webs engaged with rotary energy absorbers attached to the overhead of the vehicle. Beneath the seat bucket member, pairs of extensible and compressible energy absorbers are attached between the seat bucket member and the floor of the vehicle. Upon impact, the rotary energy absorbers and the extensible and compressible energy absorbers are arrayed to permit controlled and energy absorbing movement to reduce the probability of injury to the occupant of the seat. In the one form of the seat it accommodates itself to fore and aft forces acting upon it. In a modified form of the seat the design is optimized to accommodate these forces. In further forms of the seat the design is arranged for a sideward or lateral facing seat and the design is optimized to accommodate lateral forces.

Abstract: A propulsion system for vertical take off and landing aircraft includes a forward compressor fan (40) and an aft compressor fan (42) downstream of the forward fan and in series flow communication with the forward fan. The forward and aft fans are positioned in a central duct (26). A gas turbine engine (44) is in series flow with the forward and aft fans for driving the fans. The forward fan, aft fan and turbine engine are interconnected by a common shaft (50). A forward diverter structure (100) is positioned downstream of the forward fan and is movable between a first position for diverting exhaust from the forward fan downwardly relative to the longitudinal axis of the aircraft while simultaneously permitting the introduction of air behind the forward diverter structure but ahead of the aft fan and a second position wherein the exhaust from the forward fan is channeled through the aft fan and turbine.

Abstract: Aircraft gas-turbine engines (10) are often mounted and supported by strut type structures (12) which contain fuel, oil, electrical and hydraulic engine supply lines. The engine fan (18) is surrounded by a belt (24) made of tough flexible material designed to restrict travel of broken fan blade pieces, ingested objects or other debris (20). The forward strut section (12), adjacent the belt (24), is located outside of the maximum belt deflection envelope (26) except for the engine right and left cowl hinges (62 and 64) and its support structure (30), which structure (30) is made collapsible. This collapsible cowl hinge structure (30) utilizes mechanical fuse connections (68) which upon a dislocation force from the belt (24) allows the structure (30) to disconnect from the strut support structure (12).

Abstract: A spacecraft or transfer vehicle for transportation of a payload from a space shuttle parking orbit to a higher operation orbit, wherein the transfer vehicle utilizes housekeeping subsystems integrated into the payload, to avoid unnecessary duplication of these subsystems, for such functions as power supply, guidance, control, and communications. The transfer vehicle disclosed includes a propulsion system with at least one low-thrust bipropellant liquid rocket engine, to provide a "soft" or low-acceleration ascent, and employs two tanking stages, each having four propellant tanks, arranged symmetrically in a circular configuration. The first stage of four tanks is jettisoned during ascent, and the second stage, including the remaining four tanks, the rocket engine, and related supporting structure, is separated from the payload when the operational orbit is reached.

Abstract: A concrete marine float having a deck plate which is substantially wider than the width of the underlying casing in order to form overhanging flanges on opposite sides of the float. The flange is supported by longitudinally spaced gussets which extend from the sidewalls of the float to the underside of the deck. Utility conduits extending along the float beneath the flanges pass through the gussets and are thereby supported. The utility conduits pass upwardly through the deck to communicate with conventional utility outlets mounted on the deck.

Abstract: A V/STOL aircraft comprising a fuselage, having three sets of wings that are offset lengthwise and vertically. The center set of relatively small relatively thick wings 34 between the canard 14 and the rear relatively thin relatively large aerodynamic lift wings 18 are equipped with identical lift fans 36 enclosed in the wing by upper and lower movable slotted deflectors 40. The attitude of the slatted deflectors may be varied to transition the present invention from hovering to forward flight, and vice versa. The present invention's lift fans are interconnected by a balanced power distribution system, to insure constant, efficient use of total power and provide symmetrical lift about the aircraft's center of gravity resistibility. In the event of an engine failure, the remaining lift is still properly distributed to maintain symmetrical lift, so as to maintain balance and operational control of the aircraft in the lift mode.

Abstract: A floating device for transshipment of cargo from one ship to another comprises two pontoons (1,2) that are mutually connected and between which space is present for mooring one or more ships, such as barges, and that is adapted to moor alongside another ship, the pontoons supporting one or more structures on which devices are mounted for manipulating cargo, such as hoisting devices. This known device is useful only in quiet water, for instance within the shelter of a harbor. The invention improves the known device in such a manner that it also can be used in exposed places, so that it will be useful in bad weather and may remain in place for instance anchored to a mooring buoy or such. To this end, two pontoons (1,2) have such a small free board that it is swept over during bad weather conditions, the pontoons (1,2) being interconnected by a bow (3) extending higher than the upperdeck (5) of the pontoons.

Abstract: An improved arm restraint system for moving the arms of an ejection seat occupant to restrained positions along the sides of the occupant's torso upon initiation of emergency escape ejection of the seat and occupant from an aircraft includes a multistrap and guide ring arrangement wherein the elbow of the aircrewman is drawn tightly against the torso side through a direct interconnection therebetween and concurrently his hands/wrists are drawn to the ejection control of the seat.

Abstract: A trim indicator for outboard motors or the like for determining the tilt or angularity of the propeller with respect to a parallel position to the water level. The indicator is attached to the motor to align a vertical sensing member perpendicular to the axis of the propeller. When the motor is tilted, e.g. as the boat comes up to planing speed the sensing member indicates the angular degree of tilt by means of an electrical circuit to a signal receiver suitably located in the operating control panel in order that appropriate trimming measures may be taken. The indicator may be attached to the motor shroud or cover in the form of a signal sending housing. The sensing member may be in the form of an electrically conductive ball which seeks by gravity the lowest point on an arcuate track having a series of spaced electrical contacts.

Abstract: A water glider assembly includes two water glider members and a separate elongated stabilizer cartridge which can be inserted between the glider members to connect them together and eliminate not only lateral and vertical separations, but also individual sideways rotation of each glider member, while at the same time allow for free parallel movements therebetween. One or the other of the glider members can be partially disconnected from the stabilizer cartridge during use of the assembly so that its direction of orientation can be changed, thereby enabling the user to easily change the direction of movement of the assembly as a whole.

Abstract: A deployable inlet for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the air inlet located in the leading edge of the vertical stabilizer at such times as the center boost engine is shut down and non-operative, thus minimizing drag. More particularly, an inlet construction for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations; and/or (iii), under certain emergency operating conditions; and, wherein the air inlet for such center boost engine is located at the root leading edge of the aircraft's vertical stabilizer.

Abstract: A pin extends from the floor near a cargo door and pallets or containers are provided with an attachment which includes a releasable frame with a hinged spring-loaded plate having a bore and runoff surfaces. The bore traps the pin and forces the pallet or container to turn.

Abstract: A canopy system for deployment around the periphery of a vessel floating on a body of water is disclosed primarily for use in connection with drillships in Arctic waters.

Abstract: A parachute deployment sequencer includes two sequencer systems in electromagnetic shielding housings. Each housing contains two bellows connected to pitot tubes, a third bellows for measuring ambient pressure and three switch contact sets connected in series, each contact set being operated by one of the bellows. Each housing also contains a battery actuated by seat ejection and a deployment firing circuit with a series switch circuit in between. After ejection, deployment is initiated when all three switches are closed.

Abstract: A load such as supply containers, weapons or the like is dropped from an craft by a carrier which has a longitudinal support beam and wings which are hinged to the support beam to normally extend in the direction of the longitudinal support beam when the load is secured to the aircraft through the support beam. Once the beam with the load attached thereto is released from the aircraft the wings are automatically spread out for controlling the flight of the load to the ground. The longitudinal carrier or the load itself may be equipped with a propulsion system that may be controlled automatically by control means forming part of the load or it may be controlled by remote control.

Abstract: The disclosure relates to a vehicle that is sustained in flight solely by thrust from a jet engine and directionally controlled by shifting the center of gravity of the vehicle relative to the thrust axis of the engine.

Abstract: A hull is provided including opposite longitudinal upstanding outer sides and a central depending longitudinal displacement-type keel. The forward ends portions of the outer sides and the keel curve inwardly and upwardly, respectively, and merge to form a forwardly and upwardly tapering bow. The lower portions of the sides, rearward of the bow, terminate downwardly in downwardly and outwardly inclined outer side surfaces of opposite side downwardly and outwardly inclined displacement-type cutwaters whose lower marginal portions are rearwardly and downwardly inclined. The cutwaters include inwardly and upwardly inclined inner side surfaces extending longitudinally thereof and which diverge upwardly away from the corresponding outer side surfaces.

Abstract: A Kreuger flap is hinge-mounted to the leading edge of an aircraft wing by a plurality of hinges hinged at one end internally of the wing, near its leading edge, and at the other end to the rear surface of the Kreuger flap. A torsion tube extending longitudinally through the wing over the length occupied by the Kreuger flap and to the rear of the hinge connection to the wing, is forcibly rotated by a single hydraulic cylinder connected to a crank arm fixed to and projecting radially from the torsion tube. A coil spring fixed at one end to the wing and at its opposite end to a second arm projecting radially from one end of the torsion tube, is moved overcenter during arm movement between first and second position during Kreuger flap extension and retraction and biases the Kreuger flap towards retraction.

Abstract: Variable camber actuator assemblies 50 broaden the range of speeds at which lift to drag performance is maximized for slotted flap wings. Lift is improved over a broader range of cruising speeds by varying wing camber with rotational flap movements that do not introduce wing slots and induced drag. Forward flaps 40 are secured to forward flange links 26 which extend from, and are a part of, forward flap linkage assemblies 20. The forward flaps 40 rotate about flap pivots 39 with their rotational displacement controlled by variable camber actuator assemblies 50 located between the forward flaps and the forward flange links. Rear flaps 45 are held relative to the forward flaps 40 by rear flap linkage assemblies 70 which may act independently from the forward flap linkage assemblies and the variable camber actuator assemblies. Wing camber is varied by rotating the flaps with the variable camber actuator assemblies while the flaps are in a deployed or tucked position.