XA/EVA Project Office Weekly Activity Report 31 August 2000
Joint EVA Working Group Technical Interchange Meeting for Orlan Spacesuit
EVA working group representatives returned this week from a nine-day meeting in Moscow with the Russian spacesuit manufacturer Zvezda. The result of the meeting was a signed protocol with 23 agreements on the design, use, and maintenance of Orlan spacesuits during ground testing, crew training, and on-orbit operations.
The next meeting between these groups is planned for late October and will be held in Houston. The EVA working group representatives will discuss comments and changes to the U.S./Russian co-developed Failure Analysis documents.
Propulsion Module
The EVA Project Office has supported discussions regarding the two alternate Propulsion Module Designs. The design of choice from an EVA standpoint is the Node X concept which utilizes the Node Structural Test Article (STA). Initial discussions indicated a 2-3 foot spacer between Node X and Node 2 would be required to access the Node 2 forward zenith heat exchangers. EVA worksite analysis showed that the spacer would not be required to perform EVA maintenance. NBL development tests will be performed to confirm all worksite analysis if this option is chosen.
HTV #10 Kickoff Meeting
A Human Thermal Vacuum #10 Kickoff Meeting was held 8/25/00. Content of HTV #10 was solidified during this meeting and includes the Marshall Space Flight Center Kit for External Repair of Module ImpacTs, S0/Lab Forward Avionics Rigid Umbilical, S0 Keel Fitting, S3/P3 Solar Alpha Rotary Joint clamshell launch restraint, S3 Adjustable Diameter Pin, and use of the Metal Oxide canister as primary objectives. Secondary hardware includes the S1 Thermal Radiator Rotary Joint, Antirotation Bolt Lock Device, and S0 Secondary Power Distribution Unit Robotic/EVA door. There is concern that the S0 STA shipment to KSC may complicate access to the keel pin, which is needed to ship the article. This concern is being addressed by Boeing.
Symmetric Fluid Quick Disconnect Loads Assessment
The Engineering Directorate, Crew and Thermal Division presented data to the EVA CCB on additional loads analyses that were performed in support of the quick disconnect “line whip” issue. The assessment indicates that the previously performed “fire hose” test conducted at Boeing-Huntington Beach was not as conservative as originally thought. Based on his assessment and a review by Boeing engineers, a decision has been made to design the EVA restraint device for 900 lbf versus the originally planned value of 200 lbf. Hardware designers were given an action by the EVA CCB to come back with a status on their design at the September 22, 2000, EVA CCB.
Original signed by:
Gregory J. Harbaugh
Manager