Abstract: A method and apparatus for deploying the payload of space shuttle craft or the like. The payload rotated about an axis outside of the payload but approximately longitudinally of the cargo bay of the shuttle craft. The payload may thus be rotated, through ninety degrees. In this case, that is in its rotated position, the payload may or may not have a small portion located within the cargo bay. Alternatively, the payload may be located completely outside of the bay. According to the apparatus two separable hinge-like devices connect at one longitudinal side or edge of the payload to respective ones of the payload trunnions at different longitudinally spaced locations along the length of the payload. Separation of the payload from the cargo bay is made unlatching a latch and by the use of a repulsion spring at the position of each hinge-like device. Two four-link mechanisms allow movement between payload and bay.

Abstract: A method of effecting the in-flight departure of an astronaut from a shuttle craft, and apparatus therefor. A plurality of rocket assemblies with a lanyard for each are provided, although only one rocket assembly is used for one escape. The astronaut is carried in a parachute harness which is selectively connectible by the astronaut to one of the lanyards. A safety lever is moved when the astronaut pulls the lanyard. An ignition system is subsequently actuated when the lanyard is pulled further by the astronaut. Two rods push their corresponding rocket out through the side hatch of the shuttle craft. When the lanyard grows taut, one means fires the rocket. Subsequently, other means pull the parachute ripcord.

Abstract: A gripping device 10 for providing large moment-carrying capability for handling long cylindrical work-pieces W of a wide range of diameters. The device 10, which may be attached as an end effector for a robotic arm, includes two spaced pairs of parallel jaw type gripping members, 87, 102 and 101, 98. Each gripping member includes a gripping pad 110d with a contour which accommodates the grasping of cylindrical objects of different diameters. Movement of the gripping members between a fully open position (FIG. 3) and a fully closed position (FIG. 4) is controlled by a pair of concentrically arranged inner and outer output drive shafts 56, 59, each of which is provided with a pair of arms (81,82 and 83,84) extending in generally opposed radial directions of the shaft axis and to which a gripping member is pivotally attached near its distal end.

Abstract: A system for docking a space vehicle 11 to a space station 12 where a connecting tunnel for in-flight transfer of personnel is required. Cooperable coupling mechanisms 51, 52 include docking rings 56, 61 on the space vehicle 11 and space station 12, respectively. The space station is provided with a tunnel structure 15, a retraction mechanism 30, and a docking ring 56 attached thereto. The vehicle coupling mechanism 52 is designed to capture the station coupling mechanism 51, arrest relative spacecraft motions while limiting loads to acceptable levels, and then realign the spacecraft for final docking and tunnel interconnection. The docking ring 61 of the space vehicle coupling mechanism is supported by linear attenuator actuator devices 63 each of which is controlled by a control system (FIG.

Abstract: A microwave radar signal is generated (16) and split by a circular (20). A phase shifter (24) introduces a plurality of phase shifts into a first part of the split signal which is then transmitted (36) by antenna (34). A like plurality of phase shifts are introduced by the phase shifter into the return signal (40) from the target. The circulator delivers the phase shifted return signal and the leakage signal from the circulator to a mixer (44) which generates an i.f. signal output at the doppler frequency. The i.f. signal is amplified (46l ), filtered (54), counted (58) per unit of time and the result displayed (62) to provide indications of target sense and range rate. An oscillator (50) controls rate of phase shift in the transmitted and received signals and provides a time base for the counter. The phase shift magnitude increases may be continuous and linear or discrete functions of time.

Abstract: A block of electrically-conductive material which is to be formed into a body with internal and/or external surfaces that approximate hyperboloids of one sheet is placed so that its axis is set at a predetermined skew angle with relation to a travelling EDM electrode wire and the electrode wire is then moved into cutting proximity of the body. Thereafter, by revolving the body about its own axis, the external and/or internal surfaces of the body will be cut into an approximate hyperbolic surface of revolution depending upon whether the body is positioned with the cutting wire outside of the body or in a previously-formed longitudinal passage in the body. As an alternative technique, elongated channels can also be cut into the walls of the body by successively orienting the body to a selected number of angular positions with the electrode wire being either outside of the body or in a previously-formed passage in the body.

Abstract: Gas is vented from a non-cryogenic liquid storage tank 12 while discharging pressurized liquid from a tube 18 into the tank through a plurality of inclined jets 54, 56 circumferentially spaced about an end of a vent tube 20 positioned within the tube 18. Each jet is directed toward a central axis 72 of the vent tube, such that the end of vent tube receives gas from the vessel passing between individual jetstreams, which in combination form a conical-shaped barrier to liquid droplets which would otherwise also pass to the vent tube and out the tank 12. Gas is thus vented through the central tube while pressurized liquid flows in an axially opposite direction in the annulus between inner vent tube 20 and the outer liquid tube 18. The system of the present invention is particularly well suited for venting gas from a tank being replenished with liquid at a zero or near zero gravity environment.

Abstract: A hatch cover system including an ellipitcal port opening (12) in a housing (10) and an elliptical cover member (18) supported centrally by a rotational bearing (53) for rotation about a rotational axis (54) normal to the cover member and by pivot pins (57,62) in a gimbal member (24) for pivotal movement about axes (56 and 58) perpendicular to the rotational axis. Arm members (26,28) support the gimbal member (24) pivotally by pivot members (30,31) so that upon rotation and manipulation the cover member (18) can be articulately moved from a closed position on the port opening to an out of the way position with a minimum of volume sweep by the cover member (18).

Abstract: A bio-reactor for cell culture which provides for the introduction of fresh medium without excessive turbulent action. The fresh medium enters the bio-reactor through a filter with a backwash action which prevents the cells from settling on the filter. The bio-reactor is sealed and depleted medium is forced out of the container as fresh medium is added.

Abstract: A pyrotechnic actuated structural release device 10 which is mechanically two fault tolerant for release. The device 10 comprises a fastener plate 11 and fastener body 12, each attachable to a different one of a pair of structures to be joined. The fastener plate 11 and body 12 are fastenable by a toggle 13 supported at one end on the fastener plate and mounted for universal pivotal movement thereon. At its other end which is received in a central opening in the fastener body 12 and adapted for limited pivotal movement therein the toggle 13 is restrained by three retractable latching pins 61 symmetrically disposed in equiangular spacing about the axis of the toggle 13 and positionable in latching engagement with an end fitting on the toggle. Each pin 61 is individually retractable by combustion of a pyrotechnic charge 77, the expanding gases of which are applied to a pressure receiving face 67 on the latch pin 61 to effect its retraction from the toggle.

Abstract: The driving (30) and driven (32) members of a magnetic drive (20) are separated by an enlarged gap (35) to provide clearance for a conduit (23) or other member. Flux pins (40) in the gap (35) maintain the torque transmitting capability of the drive (20). The spacing between two of the flux pins is increased to provide space for the conduit (23).

Abstract: Apparatus and method of removing desirable constituents from an infusible material by infusion extraction, where a piston operating in a first chamber draws a solvent into the first chamber where it may be heated, and then moves the heated solvent into a second chamber containing the infusible material, and where infusion extraction takes place. The piston then moves the solvent containing the extract through a filter into the first chamber, leaving the extraction residue in the second chamber.

Abstract: A four-terminal electrical connector device (40) for testing and measuring unknown resistances of initiators (11) used for starting pyrotechnic events aboard a Space Transportation System. The testing device minimizes contact resistance degradation effects and so improves the reliability of resistance measurement taken with the device. Separate and independent voltage sensing (19) and current supply (20) circuits each includes a pair of socket contacts (13-16) for mating engagement with the pins (17,18) of the initiator. The unknown resistance that is measured by the device is the resistance of the bridgewire (23) of the initiator which is required to be between 0.95 and 1.15 ohms.

Abstract: An aerobraking orbital transfer vehicle which includes an aerobraking device which also serves as a heat shield in the shape of a raked-off elliptic or circular cone with a circular or elliptical base, and with an ellipsoid or other blunt shape nose. The aerobraking device is fitted with a toroid-like skirt and is integral with the support structure of the propulsion system and other systems of the space vehicle. The vehicle is intended to be transported in components to a space station in lower earth orbit where it is assembled for use as a transportation system from low earth orbit to geosynchronous earth orbit and return. Conventional guidance means are included for autonomous flight.

Abstract: A system for deriving direct digital indications of frequency and phase difference between two incoming pulse trains adaptable for collision avoidance systems or the like.A pair of radar beams 152 and 152A are directed toward a target 153 and corresponding beams 154 and 154A returning therefrom are detected. A digital difference circuit 110 forms a pulse train 66 from the Doppler shift frequencies of each beam pair having a repetition rate functionally related to the difference in magnitude of the shift frequencies. Pulses from the pulse train are counted as a function of time. Visual indications thereof on display 144 are correlative to target position relative to beams 152 and 152A.

Abstract: A helmet formed of a rigid shell is disclosed. The shell is lined with several air filled bladders to contact firmly the head of a user. The shell has a rigid chin bar supporting a bite bar connected fixedly to a mouthpiece bearing against the teeth and hard palate to firmly anchor the helmet without movement. The outer shell surface supports various air pumping bulbs and accelerometers. Separate left and right visor pivot on the side guided in a central tongue and groove track to move optical lens mounts into the user's field of vision. The chin bar is connected to the shell by a pair of releasable clasps. A safety lanyard connects to the clasps to quickly pull pins from the clasps to enable quick release in case of motion sickness.

Abstract: A technique for producing thrust by generating a hybrid plume plasma exhaust is disclosed. A plasma flow is generated and introduced into a nozzle which features one or more inlets positioned to direct a flow of neutral gas about the interior of the nozzle. When such a neutral gas flow is combined with the plasma flow within the nozzle, a hybrid plume is constructed including a flow of hot plasma along the center of the nozzle surrounded by a generally annular flow of neutral gas, with an annular transition region between the pure plasma and the neutral gas. The temperature of the outer gas layer is below that of the pure plasma and generally separates the pure plasma from the interior surfaces of the nozzle. The neutral gas flow both insulates the nozzle walls from the high temperatures of the plasma flow and adds to the mass flow rate of the hybrid exhaust. The rate of flow of neutral gas into the interior of the nozzle may be selectively adjusted to control the thrust and specific impulse of the device.

Abstract: An analytical technique for controlling the curing process of fiber-reinforced composite materials that are formed using thermosetting resins. The technique is the percent gel method and involves development of a time-to-gel equation as a function of temperature. From this equation a rate-of-gel equation is then determined, and a percent gel is calculated which is the product of rate-of-gel times time. Percent gel accounting is used to control the proper pressure application point in an autoclave cure process to achieve desired properties in a production composite part.

Abstract: A berthing mechanism especially for use in berthing and compliant air-tight securing between manned space vehicles and modules. The interface is provided by a pair of annular rings, one of which is typically, mechanically attached to the vehicle and the other to the module to which it is to be docked and secured. One of the two rings is attached to a base by a resilient bellows. The facing surface of one annular ring is joined to a base by a cable laced through alternating pulleys attached circumferentially so that the interface surface of that ring may be tilted to accommodate angular misalignment as said annular rings are brought into docking (berthing) contact. Interleaving guide flanges with chamfered sides provide at least some rotational misalignment correction.

Abstract: A foldable expandable pallet (10) having a basic square configuration. Each pallet is comprised of a plurality of struts (11, 13) joined together by node point fittings (12) to make a rigid structure. Some of the struts have hinge fittings (15) and are spring loaded to permit collapse of the module for stowage (26) and transport to a space station. Dimensions of the pallet are selected to provide convenient, closely spaced attachment points between the relatively widely spaced trusses (21, 30, 31) of a space station platform. A pallet is attached to a truss at four points: one close fitting hole (22); two oversize holes (24, 25); and a slot (23); to allow for thermal expansion/contraction and for manufacturing tolerances. Applications of the pallete include its use in rotary or angular joints (29); servicing of splints; with gridded plates (34); as instrument mounting bases; and as a roadbed (36) for a Mobile Service Center (MSC) (37).