Abstract: The present invention is an apparatus for directing a fluid stream from a source tube to a selected one of a plurality of outlet tubes in fluid flow communication with the source tube. Disposed within the source tube is an elongated sleeve, the sleeve having an inlet port and a single outlet port, the inlet port being in fluid flow communication with the source tube and the outlet port. The sleeve is longitudinally movable and rotatable within the source tube for selectively closing all of the outlet tubes and directing the fluid stream to a desired one of the outlet tubes. Apparatus is provided for rotating the longitudinally moving the sleeve.

Abstract: A vacuum producing device has a hollow housing with a first end having a downstream opening therein. This downstream opening has disposed thereacross a restrictive throat. The restrictive throat has a passage therethrough extending along a passage axis. This housing has a second end with an upstream wall. A suction tube is mounted through the upstream wall in the housing. The inner end of the suction tube is centrally located in the housing. The inner end of the suction tube is also aligned with and adjacent to the restrictive throat. The housing has a lateral opening. A conduit is mounted at the lateral opening to communicate with the housing. The longitudinal axis of the conduit is oriented at an acute angle with respect to the passage axis of the throat. The conduit can be connected to a blower to be pressurized thereby. This vacuum producing device has various purposes, including removal of trim produced when cutting plastic in the form of a roll.

Abstract: A fire-resistant foam having hydrogen-filled cells for use in airship/balloon envelopes.

Abstract: A digital power controller for an aircraft having a computer controlled propulsion system is disclosed. A movable handle is in electronic communication with a computer of the propulsion system. The handle is positionable is a neutral location for maintaining the aircraft at a substantially constant velocity and for resetting power command functions. The handle is also positionable in locations forward the neutral location for commanding increasing acceleration rates of the aircraft. The handle is positionable in locations aft the neutral location for commanding increasing deceleration rates of the aircraft. A switch associated with the movable handle is engagable at the forward end aft positions for commanding velocity hold and for permitting reposition of the handle to the neutral location for resetting power command functions.

Abstract: An automatically activated fire extinguishing apparatus mounted within a stove hood. The apparatus has a plastic bag liner enclosing a composition of fire extinguishing materials under pressure within a metal necked container. A pressure gauge housing having an interior channel containing an end of the plastic liner separates the necked container from an actuating header. A plastic nipple, located in a channel of the actuating header, closes an open end of an insert connected to the plastic liner. A fire sensitive device actuates a trigger which causes a cutting ram to sever the end of the nipple to permit exit of the fire extinguishing composition.

Abstract: The present invention discloses an emergency escape unit to be used in case of an emergency such as a fire, an earthquake or the like, such that the user safely escapes from a high building with the use of this escape unit. In the emergency escape unit of the present invention, a light-weight gas such as helium, air or the like, filled in a bomb may be quickly released into a sack-like canopy, causing the canopy to be expanded in the form of an umbrella, so that the air resistance during descent is quickly increased, enabling the user to fall slowly. When helium is used as the light-weight gas to be released into the sack-like canopy, provision is made such that buoyancy is generated.

Abstract: A fire-resistant container such as a courier bag or the like which provides both active and passive protection to its contents to thereby obtain a high degree of fire protection over a long period of time. Passive protection is provided by insulating walls, while active protection is obtained by disposing inside the bag a gas cylinder containing a charge of halogenated hydrocarbon. The gas cylinder is closed with a solder plug whose melting temperature is chosen in accordance with the type of material to be protected.

Abstract: A modular, pedal-type rudder, brake, and nose gear steering control assembly for an aircraft. The modules are installed below the instrument panel in the cockpit of the aircraft, thus avoiding the need for floor or bulkhead penetrations. Mechanical linkage arrangements are provided for dual side-by-side pilot stations. Adjustable positioning of control pedals relative to each pilot is provided. Pedal adjustment is accomplished by moving the pedals toward or away from a pilot along an arcuate path to an extent dependent upon the length of the pilot's legs. The arcuate path of adjustment is inclined upwardly with respect to the horizontal, providing ergometrically improved operation of the control pedals.

Abstract: An improved diverter apparatus (18) is provided for use in pneumatic conveying systems (16), in order to permit selective diversion of product to waste or recycle. The apparatus (18) includes an elongate tubular body (42) having at least one opening (48) therein; a gate (52) is situated adjacent the opening (48) for normally closing the same. A piston and cylinder assembly (62) is operatively coupled with the gate (52) for selective, remote operation of the gate (52). When the gate (52) is opened, product is diverted and does not pass the gate (52).

Abstract: An attitude control system for a stabilized geostationary satellite comprising at least one terrestrial detector (T.sub.1) and a stellar detector oriented towards the North further comprises:a processing subsystem for each of at least the normal mode (I) and the stationkeeping mode (II), adapted to be connected to the detectors and to actuators (11, 12, 13) and comprising a pre-processing module (14-16) adapted to determine for each axis i an angular offset .epsilon..sub.i between a measured angle determined from the detectors and a reference angle together with a control and correction module (18, 20) adapted to determine for each axis a corrective torque of the form:c=k.sub.i..epsilon..sub.i +h.sub.i..epsilon..sub.iwhere k.sub.i and h.sub.i are parameters specific to each axis and to each processing line,a speed .epsilon..sub.i measuring unit (24,25),and a mode selection unit (26) connecting the detectors to a selected processing line and that processing line to at least one actuator.

Abstract: A drive system for a tiltrotor aircraft that provides for the operation of both proprotors by either engine or by both engines. The drive system provides an interconnecting drive shaft that extends between and connects the engines in such a manner that power is transferred from one engine to the opposite proprotor in the case of an engine failure. Also, the arrangement provides for the operation of a redundant essential systems for the aircraft should an electrical or hydraulic system fail to operate properly.

Abstract: The invention is a circular airplane with an oblately spheroidal body which derives lift from a wall or ribbon jet exhausting over its upper surface. The jet is produced by a mixed flow fan driven by an internal combustion or gas turbine engine within the body. A fixed guide van assembly removes the swirl from the outlet flow of the mixed flow fan. The jet exiting from the fixed guide vane assembly follows the curved surface of the body, exhausting downward, and produces lift. The magnitude of lift produced in each quadrant of the airplane may be reduced for thrust vectoring by flow control gates which partially block the flow of air from the fixed guide vane assembly. Rotation control vanes introduce a controlled swirl into the flow of air from the fixed guide vane assembly to effect rotation of the airplane. Actuators for flow control gates and rotation control vanes, and a flight control system, are provided.

Abstract: A self acting pressure air pulse control valve for use with fluidizing and pneumatic conveying systems for dry particulate material comprises a housing having a chamber in which a plate type closure member and an actuating piston are disposed and interconnected by an elongated actuating rod. A spring engages the actuating rod through a pivotally supported lever and biases the closure member toward a closed position. Pressure air acts across the face of the closure member to allow the valve to crack open whereupon pressure air acting on the larger actuating piston face snaps the valve to the fully open and unrestricted flow position. A reduction in pressure of the air flowing through the valve allows the biasing spring to reclose the valve to repeat its operating cycle.

Abstract: An orbital replaceable unit, "ORU", is releasably attached to an orbital maneuverable vehicle, "OMV", by a one step fastening device. The ORU contains one part of the fastening device and the OMV the other. A drive tool, containing a motor and a driven shaft, is used to grip and carry the ORU into position with the OMV and then to actuate the one fastener portion carried by the ORU for fastening engagement with the remaining portion carried by the OMV, whereupon the drive tool may be removed.

Abstract: A fire fighting device consisting of a jet engine, or alternatively another wind-producing mechanism, with a conduit mounted thereon, the conduit having an opening so that when water or another fire retardant is directed into the conduit, the water or other fire retardant will exit the opening and enter the jet exhaust when the jet engine is in operation. The jet exhaust will carry the water or other fire retardant for a long distance, thus enabling fire fighters to propel the water or other fire retardant to distant parts of a wildfire by aiming the jet exhaust above the fire. Preferably, the jet engine is mounted in a manner allowing rotation on horizontal and vertical axes to allow it to be aimed.

Abstract: A single-size interior cabin sidewall panel fits aircraft of different sizes. The panel is fabricated so that in its "relaxed" state it has a curved configuration which requires the panel to be unbended to fit in the aircraft. Larger aircraft require more unbending of the panel than do smaller aircraft. This results in a uniform pressure across the panel which promotes a close fit between adjacent overlapping sidewall panels.

Abstract: The application of technically sensitive devices in outer space requires adequate protective shields or protective chambers which protect the payload against atmospheric radiation, thermal effects etc.The foldable structure according to the invention consists of a topological arrangement of flexible tubes which are joined to each other and form the skeleton of the shield or of the chamber. To these tubes there are attached membranes which serve as protective walls.The method of manufacturing a finished protective device uses such a foldable structure, whereby the structure is unfolded by inflation of the tubes and assumes the desired two-dimensional or three-dimensional form. The membranes are also stretched by the extension of the tubes and the interaction of the membranes and the tubes, such tubes acting as struts in the inflated condition, produces a stable structure.

Abstract: A device is disclosed for regulating a set value and/or for stabilizing elastic objects subject to spin and free to move around their axis of rotation, in particular aircraft and spacecraft. For that purpose, the regulating signals required to regulate the set value or to stabilize the freely moving objects can be obtained by means of a regulator having a transfer function with a denominator degree about three orders higher than the numerator.

Abstract: An apparatus for the discharge of powder by a fluidic propellant is suitable for use as a fire extinguisher, the apparatus including a container wherein powder and propellant is pressurized prior to use of the apparatus. Discharge of the powder and the propellant from the container is accomplished by means of a diaphragm in a wall of the container, there being a gas generator contained within a well of the container for providing an overpressure which, in combination with the pressure to which the propellant has been charged, fractures the diaphragm. Thereupon, the propellant and the powder exits the container in a homogeneous stream. The overpressure is less than approximately 30 percent, preferably 20 percent of the pressure to which the propellant and the powder are subjected during a charging of the container with the powder and the propellant. The charge pressure is in the range of 400-600 p.s.i. so as to be many times greater than the pressure of an environment external to the container.

Abstract: A throttle controller includes a manual mode where engine output is a function of throttle lever angle, and an alternatively selectable Speed Hold/Thrust Hold mode which is initiated when the throttle is placed in a center Hold position. Throttle operation during the Speed Hold mode is governed by (i) a selected speed entered at a mode control panel, or (ii) a speed existing when the lever was placed in the Hold detent, given that no speed is entered and selected at that mode control panel or (iii) a selected speed/thrust designated in a flight plan entered into the aircraft's flight management computer. During the Thrust Hold mode, the throttle controller maintains the level of thrust which existed when the throttle lever was placed in the Hold detent. When out of the Hold detent, the controller operates to control output thrust as a function of Throttle Lever Angle (TLA).