United States of America As Represented by the Administrator of Nasa

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

The United States of America As Represented by the United States

The United States of America As Represented by the Administrator

Bigelow Aerospace

Irel Solutions Group Ltd.

William C Schneider

Clarence J Wesselski

Horacio M De La Fuente

Kornel Nagy

Jasen L Raboin

Gregg A Edeen

Paul D Smith

Gary Robert Spexarth

Jon B Kahn

Christopher J Johnson

John A Schliesing

David Edwards, Jr

Reginald B Berka

Gerard D Valle

Shalini Gupta

Linda F Hess

Ozden O Ochoa

Chin H Lin

Shalini Gupta Pandya

Richard C Parish

Kriss J Kennedy

Frederick J Stebbins

James P Locke

Herbert C Kavanaugh

P James Locke

Richard H Malecki

Guy L King

Edwin E Lardizabal

James D Lester

An airship system having a flexible envelope and at least one bladder positioned therein is described. The bladder(s) provide an impervious barrier between the gas within the bladder(s) and the air exterior to the bladder(s). The envelope includes longitudinal and hoops straps weaved together in a criss-cross manner. The envelope also includes rings positioned thereon that include truss members for receiving struts for removably coupling the airship to another airship. A tri-hull delta dirigible system is also described, comprising three airships coupled together using struts and arranged in an equilateral triangle formation. The tri-hull delta dirigible system has a similar lift capacity (volume) as a conventional large mono-hull dirigible, while minimizing the detrimental bending in the center of the conventional mono-hull dirigible.

Tri-hull dirigible airship

Roadway barrier system and method are disclosed for decelerating a moving vehicle in a controlled manner and for retaining the decelerated vehicle. A net or mesh of the roadway barrier system receives and captures the moving vehicle. The net or mesh is secured to anchors by energy absorbing straps. The energy absorbing straps deploy under a tensional load to decelerate the moving vehicle, the straps providing a controlled resistance to the tensional load over a predefined displacement or stroke to bring the moving vehicle to rest. Additional features include a sacrificial panel or sheet in front of the net that holds up the net or mesh while deflecting vehicles that collide only tangentially with the roadway barrier system.

Deceleration-limiting roadway barrier

A spacecraft window assembly for providing external viewing from inside an inflatable module is claimed. The inflatable shell has a plurality of layers and each layer has a window opening. The spacecraft window assembly comprises a body, a window assembly window opening, and at least one pressure pane disposed within, and forming a substantially airtight seal with, the window assembly. The body of the window assembly is adapted for securedly receiving each one of the plurality of layers of the inflatable shell to the body of the window assembly such that the window opening in each layer of the inflatable shell is substantially aligned with the pressure pane. Further, the body of the window assembly is adapted to form a substantially air tight seal with at least one layer of the inflatable shell.

Spacecraft window assembly

An inflatable module comprising a structural core and an inflatable shell, wherein the inflatable shell is sealingly attached to the structural core. In its launch or pre-deployed configuration, the wall thickness of the inflatable shell is collapsed by vacuum. Also in this configuration, the inflatable shell is collapsed and efficiently folded around the structural core. Upon deployment, the wall thickness of the inflatable shell is inflated; whereby the inflatable shell itself, is thereby inflated around the structural core, defining therein a large enclosed volume. A plurality of removable shelves are arranged interior to the structural core in the launch configuration. The structural core also includes at least one longeron that, in conjunction with the shelves, primarily constitute the rigid, strong, and lightweight load-bearing structure of the module during launch. The removable shelves are detachable from their arrangement in the launch configuration so that, when the module is in its deployed configuration and launch loads no longer exist, the shelves can be rearranged to provide a module interior arrangement suitable for human habitation and work. In the preferred embodiment, to provide efficiency in structural load paths and attachments, the shape of the inflatable shell is a cylinder with semi-toroidal ends.

Inflatable vessel and method

A portable, collapsible hyperbaric chamber. A toroidal inflatable skeleton provides initial structural support for the chamber, allowing the attendant and/or patient to enter the chamber. Oval hatches mate against bulkhead rings, and the hyperbaric chamber is pressurized. The hatches seal against an o-ring, and the internal pressure of the chamber provides the required pressure against the hatch to maintain an airtight seal. In the preferred embodiment, the hyperbaric chamber has an airlock to allow the attendant to enter and exit the patient chamber during treatment. Visual communication is provided through portholes in the patient and/or airlock chamber. Life monitoring and support systems are in communication with the interior of the hyperbaric chamber and/or airlock chamber through conduits and/or sealed feed-through connectors into the hyperbaric chamber.

Portable hyperbaric chamber

An inflatable module comprising a structural core and an inflatable shell, wherein the inflatable shell is sealingly attached to the structural core. In its launch configuration, the wall thickness of the inflatable shell is collapsed by vacuum. Also in this configuration, the inflatable shell is collapsed and efficiently folded around the structural core. Upon deployment, the wall thickness of the inflatable shell is inflated; whereby the inflatable shell itself, is thereby inflated around the structural core, defining therein a large enclosed volume. A plurality of removable shelves are arranged interior to the structural core in the launch configuration. The structural core also includes at least one longeron that, in conjunction with the shelves, primarily constitute the rigid, strong, and lightweight load-bearing structure of the module during launch. The removable shelves are detachable from their arrangement in the launch configuration so that, when the module is in its deployed configuration and launch loads no longer exist, the shelves can be rearranged to provide a module interior arrangement suitable for human habitation and work. In the preferred embodiment, to provide efficiency in structural load paths and attachments, the shape of the inflatable shell is a cylinder with semi-toroidal ends.

Advanced structural and inflatable hybrid spacecraft module

The present invention is a dissipating protection energy system designed to receive and safely dissipate the kinetic energy from high energy fragments. The energy dissipation system dissipates energy transferred to it by the incremental and progressive rupturing at an approximately constant force of strategically placed sacrificial stitching applied to a number of high strength straps, such as an aromatic polymide fiber of extremely high tensile strength. Thus, the energy dissipation system provides a lightweight device for controlling and dissipating the dangerous and destructive energy stored in high strength fragments released by catastrophic failures of machinery minimizing damage to other critical components.

Energy absorbing protective shroud

A first space vehicle is attached with a second space vehicle which includes a rocket propulsion nozzle having a combustion chamber upstream from the nozzle throat. Apparatus 10 includes an elongate grappling arm 12 extending from the first space vehicle, a pair of inflatable bladders 16, 18 positioned about the grappling arm for engaging an inner surface of the combustion chamber upon inflation, and a pair of rear bladders 20, 22 positioned about the grappling arm for engaging an inner surface of the nozzle downstream from the combustion chamber upon inflation for aligning the grappling arm and the rocket propulsion nozzle. A pressurized fluid source 24 is provided on the first space vehicle for supplying fluid pressure to the inflatable bladders, and a fluid control valve manifold 30 selectively controls the release of pressurized fluid to the bladders. According to the method of the invention, the grappling arm is inserted into the rocket propulsion nozzle, and the control valves are actuated to first inflate the front bladders and thereby interconnect the grappling arm and the rocket propulsion nozzle. The rear bladders are subsequently inflated to align a central axis of the grappling arm with a central axis of the rocket propulsion nozzle. Inflation of the rear bladders provides an axial reaction load to balance the axial load provided by the front bladders. Attaching the vehicles in space may be controlled from the earth by activating the control valves to inflate the bladders. The cost of attaching space vehicles is significantly reduced by attaching a grappling arm on one vehicle with the existing rocket propulsion nozzle of another vehicle.

Method and apparatus for coupling space vehicles

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 pyrothechnic actuated structural release device which is mechanically two fault tolerant for release. The device comprises a fastener plate 11 and fastener body 12 each attachable to one of a pair of structures to be joined. The fastener plate 11 and the fastener body 12 are fastenable by a dual swivel toggle member 13. The toggle member is supported at one end on the fastener plate and mounted for universal pivotal movement thereon. Its other end is received in a central opening in the fastener body 12, and has a universally mounted retainer ring member 38. The toggle member 13 is restrained by three retractable latching pins symmetrically disposed in equiangular spacing about the axis of the toggle member 13 and positionable in latching engagement with the retainer ring member on the toggle member. Each pin is retractable by a pyrotechnic charge, the expanding gases of which are applied to a pressure receiving face on the latch pins to effect retraction from the ring member. While retraction of all three pins releases the ring member, the fastener is mechanically two fault tolerant since the failure of any single one or pair of the latch pins to retract results in an asymmetrical loading on the ring member and its dual povotal movement ensures a release.

Double swivel toggle release

A disc brake system for a shuttle orbiter including an annular disc element (10) having internal radially directed and angularly spaced relief slots (12) and trapezoidial shaped carbon pad members (15) disposed circumferentially around the disc element. T Clips (19, 19') snugly engage the outer ends of the pad members and are attached to rivet heads (34, 35) and (34', 35') and have guide members (51, 51') slidably received in guide grooves (50, 50') in a spring housing (20). Springs (61) provide a force tending to move the T Clips toward the center of the disc where the magnitude of the force can be adjusted by a screw (65).

Preloaded brake disc

A mobile platform (B) for transit about a working face (51) of a truss. The truss has a grid of node guide pins (54) having stationary sprockets (54D). The platform (B) has a rail system (52) comprised of transversely disposed T-shaped tracks (60), direction changing means (58) at their intersections and retractable, reversible chain drive systems (22). The chain drive (22) selectively engages the sprockets (54D) of the guide pins (54) providing selective movement of the platform (B) in two orthogonal directions (L and T). The present invention provides a near-uniform traversing velocity with minimal dynamic loading on the system. Pivoting changers (C1 and C2) move the platform (B) from one face (51) to another.

Mobile remote manipulator system for a tetrahedral truss

A triangular space station deployable in orbit. The framework is comprised of three trusses, formed of a pair of generally planar faces comprised of foldable struts which expand and lock into rigid structural engagement forming a repetition of equilateral triangles and non-folding diagonal struts interconnecting the two faces. The struts are joined together by node fittings. The framework can be packaged into a size and configuration which can be transported by a space shuttle orbiter in a single orbital flight and when deployed, provides large work/construction area and ample planar surface area for solar panels and thermal radiators. A plurality of modules are secured to the framework and then joined by tunnels to comprise an interconnected modular array disposed along the free edges of the framework. Thruster units for space station orientation and altitude maintenance are provided. The triangular space station provides a structurally stable unit having sufficiently high structural integrity and natural frequency for facilitating docking, satellite servicing and launch operations.

Shuttle-launch triangular space station

Simple apparatus for analyzing trace impurities in a gas, such as helium or hydrogen, comprises means for drawing a measured volume of the gas as sample into a heated zone. A segregable portion of the zone is then chilled to condense trace impurities in the gas in the chilled portion. The gas sample is evacuated from the heated zone including the chilled portion. Finally, the chilled portion is warmed to vaporize the condensed impurities in the order of their boiling points. As the temperature of the chilled portion rises, pressure will develop in the evacuated, heated zone by the vaporization of an impurity. The temperature at which the pressure increase occurs identifies that impurity and the pressure increase attained until the vaporization of the next impurity causes a further pressure increase is a measure of the quantity of the preceding impurity.

Gaseous trace impurity analyzer and method

An auger device is used to attach rigidized surface insulation to a spacecraft. The auger is preferably screwed into an insulation tile which has been predrilled. The augertile combination is then fastened to the spacecraft using an attachment screw which penetrates the spacecraft skin and which is secured by a blind end fastener. In an alternate method, the auger is incorporated in the insulation tile when the latter is fabricated.

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Houston, TX, United States of America

William C Schneider