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UTILIZATION OF ELASTIC RECOVERY MATERIALS FOR THE DEVELOPMENT OF CREW TRANSFER TUNNELS, AIRLOCKS, AND SPACE MAINTENANCE HANGARS. PART 2. EXPANDABLE MODULAR CREW TRANSFER TUNNEL DESIGN, FABRICATION, AND TESTING
GOODYEAR AEROSPACE CORP AKRON OH
This report summarizes the design, analysis, fabrication, and testing of the expandable Gemini to Manned Space Station MSS modular crew transfer tunnel. The program established the design of a 3.5-ft dia modular tunnel to be used as a pressurized meteoroid protective enclosure for astronauts transferring from the Gemini capsule to the MSS. The transfer tunnel attaches to the elliptical Gemini hatch at one end and to the circular MSS hatch at the other end. A prototype tunnel was fabricated and tested to establish design feasibility. Tunnel construction is a composite wall consisting of an inner triple-barrier pressure bladder for gas retention, a 4-ply Dacron cloth structural layer, a 2-in. thick polyether foam meteoroid barrier, and a film- cloth laminate outer cover with a thermal coating. The expandable composite wall is structurally bonded to a rigid aluminum honeycomb sandwich floor to which the packaging canister is attached when the tunnel is folded to constitute a modular unit. Pressure proof testing for 7 days at 10 psi and cyclic pressure testing from vacuum to the nominal operating pressure of 7.5 psi for 60 cycles established the structural integrity. Pressure leak testing under ambient conditions for 7 days at 7.5 psi established the gas tightness of the structure with a leak rate of 0.50 lbday of inflation gas under orbital conditions. Pressure leak testing in a vacuum chamber at an average vacuum of 4 x 10-5 mm Hg for one day established a leak rate of 0.40 lbday of inflation gas under orbital conditions.
Final rept. Nov 1964-Jan 1966
See also Part 1 dated Jan 1966, AD489344.
Approved for public release; distribution is unlimited. Document partially illegible.