Post on 20-Jan-2016
transcript
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)
15-16 June 2005
EWR127.1-Chapter 3Launch Vehicle, Payload, and Ground Support Equipment Documentation, Design, and Test Requirements
3.12.1.3 Flight Hardware Pressure System Offloadinga. 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.
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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
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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
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Defuel Tank 1
RV1
CV
G1
P1
V1
V4
RV2
DOT 4BW
G3
V3 P3
V2 P2 SV2
THEMIS Probe
Facility Vent
Propellant Offload Panel
Facility Vent
SV1
Tank 1 Tank 2
G2
SV3
Scrubber
Cylinder
Regulated GN2 Source
20 gal min cap
Scale
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Defuel Tank 2
Tank 1 Tank 2Facility Vent
V1 RV1 RV2
P1
CV
G1
Regulated GN2 Source
Propellant Offload Panel
V4
V2
V3
G2
G3
P2
P3
DOT 4BWCylinder20 gal min cap
Scale
SV1
SV2
SV3
THEMIS Probe
Facility Vent
Scrubber
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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.)
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Fill/vent panel
Open/close valve
Drain line or cap
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HOSE PASSED THROUGH FAIRING
DOOR DURING ENCAPSULATION
HOSE ATTACHMENT
FITTING
PROBE FUELING
VALVE
Drawings: P. Turin
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FAIRING DOOR
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VALVE OPENING WRENCH IS SLID
DOWN HOSE WHICH ACTS AS GUIDE
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FLANGE ON WRENCH PREVENTS WRENCH
FROM SLIDING BEYOND NUT
WRENCH IS TURNED TO OPEN VALVE
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HOSE REMOVING WRENCH IS SLID
DOWN HOSE, WHICH ACTS AS GUIDE
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REMOVABLE FLANGE ON WRENCH
PREVENTS WRENCH FROM SLIDING
BEYOND NUT
WRENCH IS TURNED TO
REMOVE HOSE
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FLANGE ON NUT PREVENTS HOSE
FROM FALLING THROUGH WRENCH
DURING WITHDRAWAL
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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