The United States of America As Represented by the Administrator of the

Other

The United States of America As Represented by the Administrator of

Jon B Kahn

Clarence J Wesselski

Timothy E Pelischek

Edgar O Castro

William C Schneider

Kornel Nagy

Margaret E Grimaldi

Gregg A Edeen

John P McManamen

Donald C Wade

James B McDede

David A Hamilton

Irene E Verinder

John V Rivers

Todd J McCusker

Winston D Goodrich

Bruce H Becker

A multi-color liquid display system comprising a transparent conduit and system for sequentially circulating liquids of different color and different specific gravity through the conduit to present a dynamic display such as 'raining' of one liquid into another. The circulating system includes a reservoir, a pump, device for communicating liquids in the reservoir with the transparent conduit, and device for controlling the proportionate flow of the different colored liquids from the reservoir. The display system includes a panel assembly in which a front transparent panel is bonded to a second transparent panel in spaced relation thereto and the conduit for liquids is formed in a desired configuration between the panels. The sign is illuminated by back lighting and the front panel is coated to mask all but the portions of the sign to be illuminated. The corridor can be configured with an enlarged chamber and a narrower contiguous portion with openings to the chamber whereby a first circulated liquid is received in the chamber and portions of a second different colored liquid are flowed into the chamber to simulate 'raining' therein.

Multi-color liquid display system

A hockey puck (10) for playing roller hockey on a non-ice surface. The puck includes a puck body (12) of circular cylinder configuration in which a minimum of three multi-directional roller wheel assemblies (20) are mounted in symmetrical equiangular relationship about the puck center. Each wheel assembly comprises a cylindrical wheel support body (21) mounted for rotation on a central main axle (22) parallel to the planar slide surfaces (14, 16) of the puck. Each wheel assembly (20) includes at least one set of wheels (30), each wheel journalled for rotation on its own individual axle (32) mounted in a plane perpendicular to the main axle of the wheel assembly. Each wheel support body (21) has a circular cylinder outer surface (27) of a diameter greater than the thickness of the puck body and each wheel (30) in a set has a roller surface (30a) which in a cross section co-planar with the axes of all wheels in the set describes an arc with radius of curvature which exceeds the radial distance of the cylindrical outer surface of the wheel support body (21) from its main axle (22) and is concentric with arcs described by the other roller surfaces in the set, said plurality of wheel assembles thereby allowing a rolling action of at least one of the wheels (30) whenever a force is applied to the puck with a force component parallel to the playing surface.

Roller hockey puck

The present invention is directed to methods and apparatus relating to design, construction, integration and assembly of a space station. The present invention uses pre-integrated open (unpressurized) truss segments for modular construction of the space station. Each segment includes a truss structure and utility subsystems which may be fully assembled and tested on Earth. The segments may be latched together on orbit using a remote latching system. Utility subsystems, such as solar panels and radiators, are pre-integrated into the appropriate truss segment, and are deployable from the respective truss segment on orbit. Rails run lengthwise along the assembled truss. The rails may be used with a mobile transporter for translating truss segments with respect to the spacecraft as part of the space station assembly process. The rails may also be used with a mobile transporter for carrying crew personnel, a robotic arm, and other equipment.

Pre-integrated truss space station and method of assembly

Method and apparatus for joining structures, an active structure (10) and a passive structure (12), and imposing a tensile pre-load on the joint by a remotely operable mechanism comprising a heat contractible joining element (15). The method and apparatus include mounting on the structure (10) a probe shaft (15) of material which is transformable from an expanded length to a contracted length when heated to a specific temperature range. The shaft (15) is provided with a probe head (21) which is receivable in a receptacle opening (41) formed in the passive structure (12) when the active structure (10) is moved into engagement therewith by an appropriate manipulator mechanism. A latching system (45) mounted on the structure (12) adjacent to the receptacle opening (41) captures the probe head (21) when the probe head (21) is inserted a predetermined amount. A heating coil (26) on the shaft (15) is energizable by remote control for heating the shaft (15) to a temperature range which transforms the shaft (15) to its contracted length whereby a latching shoulder (24) thereof engages latching elements (47) of the latching system (45) and imposes a tensile preload on the structural joint. Provision is also made for manually adjusting the probe head (21) on the shaft (15) to allow for manual detachment of the structures (10,12) or manual preloading of the structural joint.

Method and apparatus for preloading a joint by remotely operable means

A method of encasing a luminous translucent tubing (12,32) of a non-linear complex geometrical configuration in a transparent outer member (14,34) and forming a passage (25,35) of annular radial cross section therebetween, which method comprises coating the exterior of the tubing (12,32) with a viscous temporary material (17,47) which solidifies to provide a coating with smooth exterior surface, coating the temporary substance (17,47) with a permanent forming material in a viscous liquid state which hardens to form a rigid transparent outer member (14,34) in coextensive surrounding relation to the tubing (12,32) and its coating of temporary material (17,47), applying heat to said coating of temporary material at a temperature above the melting point of the temporary material and below the softening temperature of the outer member, and removing the temporary material from between the translucent tubing (12,32) and the transparent outer member (14,34) while supporting the translucent tubing in fixed relation to the outer member to provide a passage (25,35) defined by the annular space between the translucent tubing and the transparent outer member.

Method of encasing a non-linear atubular member

An airtight, flexible joint is disclosed for the interfacing of two pressure vessels such as between the Space Station docking tunnel and the Space Shuttle Orbiter's bulkhead adapter. The joint provides for flexibility while still retaining a structural link between the two vessels required due to the loading created by the internal/external pressure differential. The joint design provides for limiting the axial load carried across the joint to a specific value, a function required in the Orbiter/Station tunnel interface. The flex joint comprises a floating structural segment which is permanently attached to one of the pressure vessels through the use of an inflatable seal. The geometric configuration of the joint causes the tension between the vessels created by the internal gas pressure to compress the inflatable seal. The inflation pressure of the seal is kept at a value above the internal/external pressure differential of the vessels in order to maintain a controlled distance between the floating segment and pressure vessel. The inflatable seal consists of either a hollow torus-shaped flexible bladder or two rolling convoluted diaphragm seals which may be reinforced by a system of straps or fabric anchored to the hard structures. The joint acts as a flexible link to allow both angular motion and lateral displacement while it still contains the internal pressure and the holds the axial tension between the vessels.

Pressure vessel flex joint

A multi-color liquid display system comprising a liquid conduit 14 and a display apparatus operatively associated therewith. A fluid circulating system is connected to the liquid conduit 14 for sequentially circulating different colored liquids 22,24 of different specific gravities through the liquid conduit to produce the visual display either as a writing sign 10 wherein a transparent liquid conduit 14 is illuminated by luminous tubing 12 or as a fountain wherein the liquid conduit is fitted with a nozzle and mounted in a fountain basin to produce a fountain spray. The fluid circulating system includes a reservoir tank 20, a pump 36, a metering chamber 30 above the reservoir and a dispensing chamber 28 below the metering chamber, a plurality of ducts 40,42 and 48, for fluidly communicating the different strata of liquids in the reservoir 20 with the metering chamber 30, and a siphon line 52 and an air breather line 50 interconnecting the metering chamber and dispensing chamber. The open ends of the ducts 40,48, the siphon line 52 and the air breather line 50 in the metering chamber 30 are in a vertical arrangement such that the liquids 22,24 are siphoned from the metering chamber for circulation in sequence through the liquid conduit.

In the representative embodiment of the invention disclosed herein a load limiting, energy absorbing net is arranged to overlay a normally-covered vent opening in the rear bulkhead of the space orbiter vehicle. Spatially-disposed flexible retainer straps are extended from the net and respectively secured to bulkhead brackets spaced around the vent opening. The intermediate portions of the straps are doubled over and stitched together in a pattern enabling the doubled-over portions to progressively separate at a predicable load designed to be well below the tensile capability of the straps as the stitches are successively torn apart by the forces imposed on the retainer members whenever the cover plate is explosively separated from the bulkhead and propelled into the net. By arranging these stitches to be successively torn away at a load below the strap strength in response to forces acting on the retainers that are less than the combined strength of the retainers, this tearing action serves as a predictable compact energy absorber for safely halting the cover plate as the retainers are extended as the net is deployed. The invention further includes a block of an energy-absorbing material positioned in the net for receiving loose debris produced by the explosive release of the cover plate.

Load limiting energy absorbing lightweight debris catcher

A mechanism for the docking of a space vehicle to a space station where a connection for transfer of personnel and equipment is desired. The invention comprises an active docking structure on a space vehicle 10 and a passive docking structure on a station 11. The passive structure includes a docking ring 50 mounted on a tunnel structure 35 fixed to the space station. The active structure including a docking ring 18 carried by actuator-attenuator devices 20, each attached at one end to the ring 18 and at its other end in the vehicle's payload bay 12. The devices 20 respond to command signals for moving the docking ring 18 between a stowed position in the space vehicle to a deployed position suitable for engagement with the docking ring 50. The devices 20 comprise means responsive to signals of sensed loadings to absorb impact energy and retraction means for drawing the coupled space vehicle and station into final docked configuration and moving the tunnel structure to a berthed position in the space vehicle 10. Latches 60 couple the space vehicle and space station upon contact of docking rings 18 and 50 and latches 41-48 establish a structural tie between the spacecraft when retracted.

Docking system for spacecraft

A Shuttle type of aircraft (10) with an escape hatch (12) has an arcuately shaped pole housing (16) attachable to an interior wall and ceiling with its open end adjacent to the escape hatch. The pole housing 16 contains a telescopically arranged and arcuately shaped primary pole member (22) and extension pole member (23) which are guided by roller assemblies (30,35). The extension pole member (23) is slidable and extendable relative to the primary pole member (22). For actuation, a spring actuated system includes a spring (52) in the pole housing. A locking member (90) engages both pole members (22,23) through notch portions (85,86) in the pole members. The locking member selectively releases the extension pole member (23) and the primary pole member (22). An internal one-way clutch or anti-return mechanism prevents retraction of the extension pole member from an extended position. Shock absorbers (54)(150,152) are for absoring the energy of the springs. A manual backup deployment system is provided which includes a canted ring (104) biased by a spring member (108). A lever member (100) with a slot and pin connection (102) permits the mechanical manipulation of the canted ring to move the primary pole member. The ring (104) also prevents retraction of the main pole. The crew escape mechanism includes a magazine (60) and a number of lanyards (62), each lanyard being mounted by a roller loop (68) over the primary pole member (22). The strap on the roller loop has stitching for controlled release, a protection sheath (74) to prevent tangling and a hook member (69) for attachment to a crew harness.

Growing community of inventors

League City, TX, United States of America

Jon B Kahn