1. 15-16 June 2005 1. THEMIS Propellant Offload Concept M. Sholl (UCB) M. McCoullough (SAI) P. Turin (UCB) 15-16 June 2005 MIWG/GOWG(TIM) Space Sciences Laboratory Berkeley, CA (Revision A, 2 June 2005)

2. 15-16 June 2005 EWR127.1-Chapter 3 Launch Vehicle, Payload, and Ground Support Equipment Documentation, Design, and Test Requirements 3.12.1.3 Flight Hardware Pressure System Offloading a. Hazardous pressure systems shall be designed so that depressurization and drain fittings are accessible and do not create a personnel or equipment hazard for off-loading hazardous fluids at the launch complex. NOTE: This requirement is intended for contingency safing operations. b. The design goal is to be able to offload these pressure systems at any point after pressurization or loading, including the ability to offload all systems at the launch pad without demating of the spacecraft from the launch vehicle or any other disassembly of vehicle systems. c. In cases in which the Range User and Range Safety decide that design prohibits offload capability of a mated spacecraft at the launch pad, offload shall be possible within the launch complex.

3. 15-16 June 2005 P5 Access P5 is located centrally on PC Fifth door (2ft x 2ft) requested on fairing for access to P5 Accessible via standard “diving board”, defined in ICD Access difficult in SCAPE suit

4. 15-16 June 2005 Defuel Panel Regulated N2 supply Valve allows fuel tanks to be drained individually, with minimal reconfiguration EWR-dictated pressure relief valves, scrubbers, and facility vents required

5. 15-16 June 2005 Defuel Tank 1

6. 15-16 June 2005 Defuel Tank 2

7. 15-16 June 2005 Technique for propellant offload in SCAPE suit Propellant offload lines remain attached to P5, coiled and stowed until final fairing closeout. During final closeout, technician uses ICD-defined diving board to remove lines. Propellant valve may be opened, and line removed after offload, while in SCAPE suit from fairing exterior using offload extension tool Standard safety practices apply (tethering, etc.)

8. 15-16 June 2005 Fill/vent panel Open/close valve Drain line or cap

9. 15-16 June 2005 HOSE PASSED THROUGH FAIRING DOOR DURING ENCAPSULATION HOSE ATTACHMENT FITTING PROBE FUELING VALVE Drawings: P. Turin

10. 15-16 June 2005 FAIRING DOOR

11. 15-16 June 2005 VALVE OPENING WRENCH IS SLID DOWN HOSE WHICH ACTS AS GUIDE

12. 15-16 June 2005 FLANGE ON WRENCH PREVENTS WRENCH FROM SLIDING BEYOND NUT WRENCH IS TURNED TO OPEN VALVE

13. 15-16 June 2005 HOSE REMOVING WRENCH IS SLID DOWN HOSE, WHICH ACTS AS GUIDE

14. 15-16 June 2005 REMOVABLE FLANGE ON WRENCH PREVENTS WRENCH FROM SLIDING BEYOND NUT WRENCH IS TURNED TO REMOVE HOSE

15. 15-16 June 2005 FLANGE ON NUT PREVENTS HOSE FROM FALLING THROUGH WRENCH DURING WITHDRAWAL

16. 15-16 June 2005 Conclusions P5 may be defueled by SCAPE suited technicians, using aforementioned tools EWR-127.1, 3.12.1.3b describes this defuel capability as a goal Range and Boeing to decide whether this should be baselined, or to invoke EWR-127.1, 3.12.1.3c, which allows defueling after fairing removal