THEMIS Propellant Offload Concept M Sholl UCB M
THEMIS Propellant Offload Concept M. Sholl (UCB) M. Mc. Coullough (SAI) P. Turin (UCB) 15 -16 June 2005 MIWG/GOWG(TIM) Space Sciences Laboratory Berkeley, CA (Revision A, 2 June 2005) 15 -16 June 2005 1 .
EWR 127. 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. 15 -16 June 2005
P 5 Access • P 5 is located centrally on PC • Fifth door (2 ft x 2 ft) requested on fairing for access to P 5 • Accessible via standard “diving board”, defined in ICD • Access difficult in SCAPE suit 15 -16 June 2005
Defuel Panel • Regulated N 2 supply • Valve allows fuel tanks to be drained individually, with minimal reconfiguration • EWR-dictated pressure relief valves, scrubbers, and facility vents required 15 -16 June 2005
Defuel Tank 1 15 -16 June 2005
Defuel Tank 2 15 -16 June 2005
Technique for propellant offload in SCAPE suit • • • Propellant offload lines remain attached to P 5, 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. ) 15 -16 June 2005
Fill/vent panel Drain line or cap Open/close valve 15 -16 June 2005
Drawings: P. Turin PROBE FUELING VALVE HOSE ATTACHMENT FITTING HOSE PASSED THROUGH FAIRING DOOR DURING ENCAPSULATION 15 -16 June 2005
FAIRING DOOR 15 -16 June 2005
VALVE OPENING WRENCH IS SLID DOWN HOSE WHICH ACTS AS GUIDE 15 -16 June 2005
FLANGE ON WRENCH PREVENTS WRENCH FROM SLIDING BEYOND NUT WRENCH IS TURNED TO OPEN VALVE 15 -16 June 2005
HOSE REMOVING WRENCH IS SLID DOWN HOSE, WHICH ACTS AS GUIDE 15 -16 June 2005
REMOVABLE FLANGE ON WRENCH PREVENTS WRENCH FROM SLIDING BEYOND NUT WRENCH IS TURNED TO REMOVE HOSE 15 -16 June 2005
FLANGE ON NUT PREVENTS HOSE FROM FALLING THROUGH WRENCH DURING WITHDRAWAL 15 -16 June 2005
Conclusions • P 5 may be defueled by SCAPE suited technicians, using aforementioned tools • EWR-127. 1, 3. 12. 1. 3 b 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. 3 c, which allows defueling after fairing removal 15 -16 June 2005
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