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  • 1
    facet.materialart.
    Unknown
    Method and apparatus for preloading a joint by remotely operable means (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The invention is a method and apparatus for joining structures, an active structure and a passive structure, and imposing a tensile pre-load on the joint by a remotely operable mechanism comprising a heat contractible joining element. The method and apparatus include mounting on the structure, a probe shaft of material which is transformable from an expanded length to a contracted length when heated to a specific temperature range. The shaft is provided with a probe head which is receivable in a receptacle opening formed in the passive structure, when the active structure is moved into engagement therewith by an appropriate manipulator mechanism. A latching system mounted on the structure adjacent to the receptacle opening captures the probe head, when the probe head is inserted a predetermined amount. A heating coil on the shaft is energizable by remote control for heating the shaft to a temperature range which transforms the shaft to its contracted length, whereby a latching shoulder thereof engages latching elements of the latching system and imposes a tensile preload on the structural joint. Provision is also made for manually adjusting the probe head on the shaft to allow for manual detachment of the structures or manual preloading of the structural joint.
    Keywords: MECHANICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Pressure vessel flex joint (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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 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 returned 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 holds the axial tension between the vessels.
    Keywords: MECHANICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Load limiting energy absorbing lightweight debris catcher (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the representative embodiment of the invention disclosed, 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.
    Keywords: SPACE TRANSPORTATION
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Docking system for spacecraft (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mechanism is disclosed for the docking of a spacecraft to a space station where a connection for transfer of personnel and equipment is desired. The invention comprises an active docking structure on a spacecraft and a passive docking structure on the station. The passive structure includes a docking ring mounted on a tunnel structure fixed to the space station. The active structure includes a docking ring carried by an actuator-attenuator devices, each attached at one end to the ring and at its other end in the spacecraft payload bay. The devices respond to command signals for moving the docking ring between a stowed position in the spacecraft to a deployed position suitable for engagement with the docking ring. The devices comprise means responsive to signals of sensed loadings to absorb impact energy and retraction means for drawing the coupled spacecraft and station into final docked configuration and moving the tunnel structure to a berthed position in the spacecraft. Latches couple the spacecraft and space station upon contact of the docking rings and latches establish a structural tie between the spacecraft when retracted.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NAS 1.71:MSC-21327-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Orbiter escape pole (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: 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.
    Keywords: Aeronautics (General)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Docking system for spacecraft (1990)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: 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.
    Keywords: Aeronautics (General)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Shock-Absorbing, Retractable Docking Mechanism (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Report contains description and drawings of conceptual docking mechanism joining Space Shuttle orbiter with proposed Space Station. New version saves considerable weight. Docking module left on Space Shuttle after assembly, and only docking mechanism carried aboard Space Shuttle.
    Keywords: MACHINERY
    Type: MSC-21327 , NASA Tech Briefs (ISSN 0145-319X); 14; 8; P. 61
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    Blast-Absorbing Bag (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Proposed expandable bag contains debris from explosion. Permanently surrounds vessel or devices prone to explosive disintegration or slipped around small bomb. Finned cells shaped like outward-opening cups. Cells built up from overlapped sheets of fabric and stitched together to form expandable polyhedral bag. Cells pentagonal, triangular or square.
    Keywords: MECHANICS
    Type: MSC-21666 , NASA Tech Briefs (ISSN 0145-319X); 16; 2; P. 75
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    Net Catches Debris From Explosion (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Device restrains fragments and absorbs their kinetic energy. Net of stitched webbing folds compactly over honeycomb plug. Attaches to frame mounted on wall around rectangular area to be cut out by explosion. Honeycomb panel absorbs debris from explosion and crumples into net. Dissipates energy by ripping about 9 in. of stitched net. Developed for emergency escape system in Space Shuttle, adaptable to restraint belts for vehicles; subjecting passengers to more gradual deceleration and less shock.
    Keywords: MECHANICS
    Type: MSC-21562 , NASA Tech Briefs (ISSN 0145-319X); 16; 2; P. 76
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    Simulating A Massive, Mobile Structure (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Simulator replicates, kinematically and dynamically, mating of large, massive mobile structure with similarly large and massive fixed structure. Developed for testing berthing-and-latching mechanism. Fixed section holds active berthing-and-latching mechanism and its motor control system with optical encoder to maintain synchronization among four latches in mechanism. Tripodal load-cell network gathers data on load history of berthing operation, and infrared tracking system including light-emitting diodes produces data for position history.
    Keywords: MECHANICS
    Type: MSC-21482 , NASA Tech Briefs (ISSN 0145-319X); 14; 9; P. 72
    Format: text
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    NASA TECHNICAL REPORTS
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