27
1
1
For current baseline refer to SSP 54100 Multi-Increment Planning Document (MIPD)
MRM2
MRM1
(SM Zenith)
(FGB Nadir)
DC-1/ MLM/
RS Node
SM-Aft
Node-2 Zenith
Node-2 Nadir
N2 Fwd
Port Utilization
2013 2014 2015 Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec Jan Feb
32S
3/15
146 / 144
33S
5/14
167 / 167
34S
3/29 9/11
166 / 164
35S
5/30 11/10
168 / 166
36S
9/27
3/12
2/7
188 / 188 11/15 5/14
174 / 172
38S
3/28 7/20
9/16
173 / 171
39S
5/30 11/17
167 / 165
40S
10/2
166 / 164
41S
12/3
148 / 138
ATV4
6/15 10/31 180 / 172
ATV5
4/20 10/9
3R (MLM) 12/20
6R (RS-Node) 6/26
HTV4
8/9 9/8
HTV5
7/6 8/5
SpX-2
3/3 3/25
SpX-3
11/13 12/13
SpX-4
4/8 5/8
SpX-5
8/10 9/9
SpX-6
12/7 1/6
Orb-D1
6/10 7/5
Orb-1
9/15 10/15 Orb-2
12/11 1/10
Orb-3
4/8 5/8
Orb-4
10/6 11/5
Orb-5
1/18 2/17
49P
4/15
50P
51P
4/26
7/21
52P
7/26 12/18
53P
11/23 4/9
55P
4/30 6/23
56P
7/26 12/30
57P
10/24
58P
2/4
3/28 34S
TMA-08M
5/28 35S
TMA-09M
9/25 36S
TMA-10M
11/7 37S
TMA-11M
3/26 38S
TMA-12M
5/28 39S
TMA-13M
9/30 40S
TMA-14M
12/1 41S
TMA-15M
6/5 ATV4
4/12 ATV5
6/24 6R
RS-Node
NET 8/4 HTV4
7/1 HTV5
11/11 SpX-3
4/6 SpX-4
8/8 SpX-5
12/5 SpX-6
4/17 Orb-TF
6/5 Orb-D1
9/12 Orb-1
12/8 Orb-2
4/5 Orb-3
10/3 Orb-4
1/15 Orb-5
4/24 51P
M-19M
7/24 52P
M-20M
11/21 53P
M-21M
2/5 54P
M-22M
4/28 55P
M-23M
7/24 56P
M-24M
10/22 57P
M-25M
2/2 58P
M-26M
R-32
4/19
R-33
~6/26
U-21, 22u/r
Jul
R-34, 35
Aug
R-36
Nov 9
R-37
Dec
R-38, 39
Jan
R-40,41,42
Feb
R-43
Apr
R-44
Jun
R-45,46,47
Aug
R-48
Jan
06/01 - 06/10 07/31 - 08/08 11/01 - 11/08 12/29 - 01/08 05/29 -06/08 07/28 -08/06 10/29 - 11/06
Inc
Inc 35 Inc 36 Inc 37 Inc 38 Inc 39 Inc 40 Inc 41 Inc 42
HTV4: MBSU, UTA, STP-H4 SpX-3: HDEV, OPALS
SpX-4: RapidScat HTV5: CALET, CATS
SpX-5: CREAM SpX-6: SAGE Hexapod, SAGE NVP, MUSES
N K.
(32S)
R O.
(32S)
R E.
(32S)
C C. Hadfield (CDR-35) 146 days
(33S)
R R. Romanenko 146 days
(33S)
N T. Marshburn 146 days
(33S)
R P. Vinogradov (CDR-36) 167 days (34S)
R Misurkin 167 days (34S)
N Cassidy 167 days (34S)
R F. Yurchikhin (CDR-37) 166 days N K. Nyberg 166 days A L. Parmitano 166 days
R O. Kotov (CDR-38) 168 days (36S)
R S. Ryazanskiy 168 days (36S)
N M. Hopkins 168 days (36S)
J K. Wakata (CDR-39) 188 days (37S)
N R. Mastracchio 188 days (37S)
R M. Tyurin 188 days (37S)
N S. Swanson (CDR-40) 174 days (38S)
R A. Skvortsov 174 days (38S)
R O. Artemyev 174 days (38S)
R M. Suraev (CDR-41) 173 days (39S)
N R. Wiseman 173 days (39S)
E A. Gerst 173 days (39S)
N B. Wilmore (CDR-42) 167 days (40S)
R Y. Serova 167 days (40S)
R A. Samokutyayev 167 days (40S)
N T. Virts (CDR-43) 166 days E S. Cristoforetti 166 days R A. Shkaplerov 166 days
Stage EVAs Stage S/W
Soyuz Lit Landing
Launch Schedule
Solar Beta >60 External Cargo
05/25 06/15 07/23 08/15 09/17 10/22 11/13 12/23 05/27 07/25 09/19 11/15
22 d 25 d
11/7
54P
37S
3/25
6/11
1/12
#3-8 #3-8 #3-8 #3-8
6/16 -18 ATV4
8/15, 17-18
#3-76
DO01: DO02:
#3-8
#3-7 (Beta)
#3-75 #3-75
ICU 4/2, 4/11
X2R12.1 3/17
X2R13 9/15
#3-8
#3-7 (Beta)
#3-80
SM 8.07 9/9u/r
SpX-2 3/1
#3-8 #3-8 #3-8 #3-8
3R 12/11
MLM
#3-81
#3-7 (TDRSS)
#3-73 #3-7 (beta)
30 d 30 d
30 d
30 d
30 d
30 d 30 d 30 d 30 d 30 d 30 d
#3-7
ISS Flight Plan NASA: OC4/John Coggeshal l
MAPI: OP/Scott Pau lChart Updated: April 3rd, 2013
SSCN/CR: 13681A + Tact. Mods (In-Work)
Ø
Ø
Ø
Ø Ø
Ø
4-Orbit Rendezvous
On March 28, the 34 Soyuz vehicle with the Expedition 35 Crew launched from Baikonur. Approximately 6 hours later the Crew docked to the ISS. This was the first crewed 4-orbit rendezvous to the ISS. From the USOS perspective, docking timeline is essentially identical for either rendezvous
System configurations (powerdowns, array positioning, attitude control handover) occur at same time relative to docking and are identical to any other Soyuz No changes to joint Flight Rules or USOS procedures for the 4-orbit rendezvous
U.S. and Russian flight control and engineering teams have performed standard analysis for both 4-orbit and 34-orbit dockings Soyuz generically retains enough propellant margin to support a re-rendezvous after an abort from any point in the trajectory
3
4-Orbit Rendezvous
Ø On February 21, 2013 the ISS Program conducting it Stage Operational Readiness Review and on March 6, NASA conducted the Flight Readiness Review Ø Included detailed review of all aspects of 4 orbit Rendezvous
Ø Vehicle configurations / timelines for 4 and 34 orbit Crew fatigue and health management Ø
Ø US and RS doctors approved a sleep shifting profile to align with launch / docking activities. Crew activities post ingress were limited to the Safety briefing. Ø
Ø Space Adaptation Syndrome – discussed with combined US / Russian medical team. Ø Mitigated with experience crew members, preflight testing of medications, and the
availability of these medications to the crew on day of launch. Ø Confined space / spacesuit issues
Ø crew was allowed to ingress the Orbital Compartment for hygiene and food / water access. MAGs were approved and available to all crew members Crew able to loosen straps on-orbit to allow stretching and mitigate join pain.
Ø Ø
Ø Ø The ISSP and then the FRR Board approved the 4 – orbit for 34S only.
Ø Plan is to conduct post flight lessons learned from vehicle, ops, crew, and medical teams to understand fully the risks and to determine if 4-orbit rendezvous should be approved in the future.
4
Expedition 35/36 Overview
Expedition 35 Chris Hadfield (CDR) Roman Romanenko
Tom Marshburn (33S-Soyuz TMA-07M)
Expedition 36 Pavel Vinogradov (CDR) Alexander Misurkin Chris Cassidy (34S-Soyuz TMA-08M) 5
MRM1
SM Aft
N2 Nadir
FE-1 O. Novitskiy
FE-2 E. Tarelkin
CDR K. Ford
3/15 32S Undock
32S
Stage 34-6
FPIP SSCNs 13706/13681A IDRD Rev A CR13583
Stage 36-6 (104 Days)
Stage 35-3 Stage 35-6 Stage 36-3 Stage 36-6
Ut ilizat ionInc Ave 35
hrs / wk
More than 75 invest igat ions duringStage 35-3 and 35-6New Invest igat ions: BP reg, Car lage,FASES, ICE-GA, and UVP-2R
More than 75 invest igat ions during Stages 36-3 and 36-6New Invest igat ions: Microbiome, ICE-GA, Diapason, STP-H4, RINGS,Ocular Health, Skin-B, Space PUP, and Asian Seed.
EVA,Resupply
&Outf it ting
RS EVA #32:Obstanovka exp.Setup, ATV reflectorR&RR&O: Install ICU,iPEHG, High Def init ionCameras
RS EVA #33: R&R FGB thermal regulator panel, photoexternal surfaces of the RS MLI, remove the Foton- Gamma from Molniya-Gamma experimentUSOS EVA #36-1: MLM Pwr cable, SGTRC-2 R&R, Grapple Bar, MISSE8 & ORMatE retrieval, Z1 Jumper (1 of 2)USOS EVA #36-2: RGB V-Guides, MLM Ethernet cable, Z1Jumper, R&R JEF Fwd Cam, FGB PDGF 1553RS EVA #34: Route power from FGB to MRM2, routeEthernet cable for MRM2RS EVA #35: Set up the portable workstat ion, the two-axial target ing platform, and the medium resolut ioncamera (MRC) on the Plane IV portable workstat ionR&O: Install HTV4 H/W: JEM LAN, JEM EnvironmentalMonitor Equip, Ut ility Bonding Point, Cooler Box
E 35 CDR - C. Hadf ield (Inc 35 60 days)E 35 FE-4 - R. Romanenko (Inc 35 60 days)E 35 FE-6 - T. Marshburn (Inc 35 60 days)
E 36 FE-4 - F. Yurchikhin (Inc 36 - 104 days)E 36 FE-5 - L. Parmitano (Inc 36 - 104 days)
E 36 FE-6 - K. Nyberg (Inc 36 - 104 days)
3/29 34S Dock
Stage 35-3 (14 Days)
9/11 34S Undock
N2 Zenith
DC-1
E35 FE-1 /E36 CDR - P. Vinogradov (Inc 35 - 46 days, Inc 36 - 120 days)E35/E36 FE-2 - A. Misurkin ( Inc35 - 46 days, Inc 36 - 120 days)
E35/E36 FE-3 - C. Cassidy (Inc 35 - 46 days, Inc 36 - 120 days)
Stage 36-3 (16 Days)
Stage 35-6 (45 Days)
RS #32 April 19, 2013
Mar-2013 Apr-2013 May-2013 Jun-2013 Jul-2013 Aug-2013 Sep- 2013
Inc 34 Inc 37
51P26-April 21-July 52PATV4
RS #34
MRM2
RS #33
Orb-1
15 - Sept Berth
RS #35
HTV49-Aug Berth
8-Sept Unberth
33S 14- May
34S 11-Sept 29- Mar 3/15 Undock
Increment 36 Increment 35
35S30-May
49P 15-Apr
50P 23-Apr
Orb-D1 5-July Unberth
17-June Berth
5/30 35S Dock
5/14 33S Undock
33 Soyuz Crew
Mar
shbu
rn
Rom
anen
ko
Had
field
35 Soyuz Crew
Nyb
erg
Par
mita
no
Y
urch
ikhi
n
26-July
34 Soyuz Crew
Cas
sidy
Mis
urki
n
Vin
ogra
dov
SpX-2 25-Mar Unberth
USOS 36 - #1 & 2 July 2013
6
it
ISS Expedition 35 Mission Objectives
Perform an average of 35 hrs/week for payload investigations
FASES Invest igates the emulsion stability in relat ion to the physical-chemistry of droplet interfaces to obtain a modeling ofemulsion dynamics to be transferred to industrial applicat ionson Earth.
BP Reg Will test the eff icacy of an in-flight manipulat ion ofarterial blood pressure (BP) as an indicator of post-flightresponse to a brief stand test.
Microbiome This study will carry out a thoroughevaluat ion of how long-term space travel impacts the humanmicrobiome and ult imately human health, and it will form thebasis for further studies towards the design of therapies tomitigate any microbiome changes or related health issuesfound as a result of this project.
Ocular Health Collect evidence to characterize the riskand define the visual changes and central nervous system (CNS)changes observed during a six month exposure to microgravityincluding postflight time course for recovery to baseline.
Tritel Characterizes the radiat ion environment within the Columbus module of the ISS with high accuracy. It uses acombinat ion of three different detector types measuring theradiat ion amount, direct ion and history to determine absorbeddose and dose equivalent from solar and galat ic radiat ion.
Support visiting vehicle traffic including: SpaceX-2 unberthing, planned March 25th
34 Soyuz docking, planned March 30th, first Soyuz to perform a 4-orbit rendezvous prof ile. 49 Progress undocking, planned April 15th RS EVA #32, planned April 19th 50 Progress undocking, planned April 23rd 51 Progress docking, planned April 26th ATV-4 docking, planned May 1st
Installation of Ku Comm Unit Will increase hi rate Ku downlink from 150 Mbps to 300 Mbps, adds S/G3 and S/G4 (audio), adds two more channels of downlink video, reduces video bandwidth consumption (using new encoder algorithm), provides increased solid state recording of payload and video data.
Space-X Dragon capsule approaching and berthed to the ISS
7
Orb-D1 )
0.00
100.00
200.00
300.00
400.00
500.00
600.00
700.00
800.00
900.00
1000.00
0
10
20
30
40
50
60
70
80
0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26
Cum
ulat
ive
Sche
dule
d Cr
ew T
ime
(Hou
rs)
Wee
kly
Crew
Tim
e (H
ours
)
OOS Planned USOS Executed 35 Hrs/Wk Avg Requirement
OOS Planned Cumulat ive USOS Cumulat ive Extended
SpX-2(1/20/13 - 2/19/13)SpX-1(10/11/12 - 10/28/12)
)
ATV3 (Undock on 9/25/12) (Undock on 9/28/12)
US EVA #20 11/1/12) * CONT
(3/3/13 Inc 35)
Pre-Decisional, For Internal Use Only
Inc 36
Increment 33_34 Utilization Crew Time
Executed through Increment Wk (WLP week) 25 = 25.0 of 24.8 work weeks 100.81 % through the Increment
USOS IDRD & OOS Allocation: 868.0 hours Additional USOS Allocation for Stage 34-6: 928.0 hours (Additional 60 hours)
USOS Actuals: 938.73 hours 101.2 % through updated Stage 34-6 Allocation 108.1 % through IDRD and OOS Allocation
Total USOS Average Per Work Week: 37.55 hours/work week Voluntary Science Totals to Date: 5.08 hours (Not included in the above totals or graph)
OC/OZ reconciliation is
complete through Week 25 with the exception of ESA
time.
Date Color Key: Completed 33-34 Final OOS FPIP Plan
0.00
100.00
200.00
300.00
400.00
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30
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1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26
Cum
ulat
ive
Sche
dule
Cre
w T
ime
(Hou
rs)
Wee
kly
Crew
Tim
e (H
ours
)
OOS PLanned USOS Executed 35 Hrs/Wk Avg Requirement
OOS Planned Cumulat ive USOS Cumulat ive Executed
%%
%%
Increment 35_36 Utilization Crew Time
%SpX-2
Orb-D1
ATV4 US EVA
3-Crew 6- Crew 3-Crew 6-Crew Increment 35 Increment 36
March April May June July August Sept
US EVA
(Unberth on 3/24/13) (Unberth on 3/25/13)
(Berth on 5/8/13) Below the line
(Dock on 5/1/13)
HTV4
Pre-Decisional, For Internal Use Only
Date Color Key: Completed 35-36 Final OOS FPIP Plan
OC/OZ reconciliation
completed as of Week 2.
(Berth on6/10/13)
(Dock on 6/15/13) (8/9/13 - 9/8/13)
Executed through Increment Wk (WLP week) 2 = 2.0 of 24.4 work weeks 8.20 % through the Increment
USOS IDRD Allocation: 875 hours OOS USOS Planned Total: 876.5 hours
USOS Actuals: 81.41 hours 9.3 % through IDRD Allocation 9.3 % through OOS Planned Total
Total USOS Average Per Work Week: 40.71 hours/work week Voluntary Science Totals to Date: 0.00 hours (Not included in the above totals or graph)
ISS Research Statistics as of Feb 28, 2013
Number of USOS Invest igat ions for 35/36 : 140
0%
10%
20%
30%
40%
50%
60%
70%
80%
90%
100%
CSA ESA JAXA NASA/US
82 NASA/U.S.-led invest igat ions58 International-led invest igat ions30 new USOS invest igat ions
Over 400 invest igatorsrepresentedOver 500 scient if ic resultspublicat ions (Exp 0 - present)1 CSA
4 ESA Roscosmos data st ill in work
7 JAXA18 NASA/U.S.
ISS Research Disciplines by Partner AgencyIncrements 35/36
Biology and Biotechnology
Earth and Space Science
Educat ional and Cultural Act ivit ies
Human Research
Physical Science
Technology
TBD
9 20 29 82
Number of Invest igat ions Expedit ion 0-32: 1549* *USOS + Roscosmos10
Total ISS Consumables Status: Total On-orbit Capability 28-March-13 51P SORR, 51P (Dock 26-Apr-13)
T1: Current Capability with no resupply T2: Current Capability with 51P
Consumable – based on current, ISS system status Date to Reserve Level Date to zero supplies Date to Reserve Level Date to zero supplies
Food – 100% (1) (2) September 28, 2013 November 13, 2013 October 18, 2013 December 10, 2013
KTO June 11, 2014 July 26,2014 August 1, 2014 September 15, 2014
Filter Inserts October 9, 2014 December 2, 2014 (2) December 1, 2014 January 15, 2015
Toilet (ACY) Inserts (2) April 15, 2014 June 6, 2014 May 11, 2014 July 1, 2014
EDV (UPA Operable) (2) (3) (4) August 21, 2013 November 9, 2013 November 29, 2013 February 7, 2014
Consumable - based on system failure
EDV (UPA Failed) (3) July 16, 2013 August 30, 2013 September 10, 2013 October 31, 2013 (2)
Water, if no WPA (Ag & Iodinated) (2) (5) August 24, 2013 October 16, 2013 October 12, 2013 December 4, 2013
O2 if Elektron supporting 3 crew & no OGA (2) (6) July 5, 2013 December 2, 2013 July 18, 2013 December 15, 2013
O2 if neither Elektron or OGA (2) (6) May 1, 2013 July 6, 2013 May 7, 2013 July 13, 2013
~18 Days LiOH (7)
(CDRAs and Vozdukh off) ~4 Days ~18 Days ~4 Days
(1) Includes food on Soyuz; after RS goes to zero, both sides share USOS food. (2) Reserve level to Zero is different than 45 days due to varying crew size. (3) Progress tanks included in assessment for urine dumping only. (4) A-RFTA operations as of 8/6/12. Assumes 74% recovery rate and no RS urine processing. (5) RS processes all condensate in event of WPA failure. (6) Includes metabolic O2 for 45 day/6-crew reserve and the O2 for greater of CHeCs or 4 contingency EVAs. (7) LiOH Canisters will be used for CO2 removal from the ISS if the CDRAs are inoperable. Total LiOH Reserve Level is 14 days for 6 crew. (Reserve Level for USOS LiOH is ~13.3 days for 3 crew (20 canisters), and for RS LiOH is 15 days for 3 crew (15 canisters).) 11
USOS System Challenges
Ø Photovoltaic Thermal Control System (PVTCS) 2B Ammonia Leak - Monitoring Ø In 2007 it was confirmed that the Channel 2B PVTCS exhibited a relatively constant leak rate of ~1.5 lbm/
year that later accelerated to between 5.8 and 9.5 lbm/year by late 2012. USOS EVA 20 was performed on 11/1/12 to isolate the 2B Photovoltaic Radiator (PVR) and provide cooling via the Early External Active Thermal Control System (EEATCS) PVR via jumpers. Trending has confirmed that the isolated 2B PVR is not leaking. The new combined (hybrid) system is operating nominally. However, initial behavior suggests that the hybrid system is leaking and characterization of the rate is underway. Data to date indicates a rate in the range of ~5 lbm/yr, but many months are required to develop a reliable trend.
Ø Sequential Shunt Unit (SSU) 1A Power on Reset (POR) - Monitoring Ø On 1/10/13, SSU 1A started experiencing PORs during insolation passes, with this series of PORs ending
on 1/13/13. Previously SSU 1A had experienced 3 other PORs. The impact from these PORs has been minimal. When the SSU performs a POR, the primary power channel momentarily goes to battery power (approx 1.5 seconds). Data gathering activities were developed that could assist the team in characterizing the issue if the PORs start re-occurring. The SSU will be operated as is while specialist continue their investigation through a similar solar beta period in March. Should the SSU have a hard failure, the Flight Control Team will perform the Seamless Power Channel Handover procedure to continue providing power to the loads on this channel.
Ø Ku-Band Antenna Group 2 (AG2) Forward Link Anomaly – Troubleshooting Ø On GMT 351, the Ku-band Group 2 failed to acquire TDRS. The Ku-band was configured to open loop
pointing, with success in acquiring the return link, but not the forward link. Ku-band swapped to Antenna Group 1, acquiring TDRS nominally. Antenna Group 2 is currently powered off, with heaters enabled. Root cause identified a suspect failure in the Space to Ground Transmitter Receiver Controller (SGTRC). A spare SGTRC is available on-board. Removal and replacement is planned for US EVA #21 in June ‘13.
12
Ø Ø
Ø Ø
Ø
USOS System Challenges
Loss of Columbus Water Pump Assembly (WPA2) - Monitoring On 1/13, ESA was not successful in switching the active Internal Thermal Control System pump from WPA1 to WPA2. The switch over is a nominal activity in support of WOOV cycling conducted on a 3-month interval. Attempts to start WPA2 were unsuccessful, so the Columbus module is operating on WPA1 with no redundancy. Engineering evaluation of the fault is in-work, but the cause of the anomaly is not understood yet. A coolant top-off was performed on 2/14/13 to accommodate coolant sampling as well as margin for nominal leakage. There is no spare WPA on-board. A spare is scheduled to launch on ATV4.
Increased N3 Common Cabin Air Assemblies (CCAA) Indications - Workaround Water carryover events due to degraded heat exchanger (HX) in N3 CCAA. No spare CCAA HXs on orbit; one targeted for manifesting on HTV5. FR Waiver in work to increase time prior to Carbon Dioxide Removal Assembly (CDRA) command to standby in the event of a continuous wet indication
13
USOS System Challenges
Ø MERLIN2 Shutdown Due to False Fire Alert - Troubleshooting
Ø Event believed to be a result of a radiation hit on this system (Station at high latitude). MERLIN 2 used for galley food storage and has remained unpowered. Procedure in work to check the current system status after power up.
Ø Space Acceleration Measurement System II Remote Triaxial Sensor/Drawer 2 (SAMS-RTS/D2) Loss of Health and Status – Troubleshooting
Ø On 2/11, SAMS-RTS/D2 lost health and status. Log files show no communication between SAMS and ICU. Troubleshooting isolated issue to either ER4 PEHB or JAXA LEHX. MART identified additional troubleshooting steps to be performed on 3/26 to isolate to one of these two systems.
Ø MBSU 2 RBI 5 Trip (feeds Russian Segment Service Module [CHT] 21 & 22) – Troubleshooting
Ø Noise from the [CHT]s is believed to have caused MBSU2 RBI5 to trip off on GMT 206. Team developing procedures to use on-orbit oscilloscope to test the input side of the [CHT]s in the April/May timeframe.
14
USOS System Challenges
Ø Dragon Draco Thruster Check Valve Ø During the SpX-2 mission, 3 of 4 propulsion manifolds were not properly pressurized following
second stage separation. The issue was overcome real-time and SpaceX has identified root cause due to failure of in-line check valves. SpaceX is working design modification for follow-on missions During approach and release/departure, 3 of 4 quads are required to complete operations. An abort to protect ISS requires 2 of 4 thruster quads to be operational. Analysis has shown that Dragon will safely drift away from ISS in the event that all four quads failed Although check valves operated nominally upon entry into ISS ellipsoid, sufficient blowdown was available should an abort be required Check valve operated nominally for departure and re-entry
Ø
Ø
Ø
Ø HTV3 Abort Ø The HTV3 abort was caused by an interaction between the grapple fixture cam arms on the
vehicle and the initial motion of the SSRMS during back away due to the relative positions of the HTV and the ISS. This interaction created rates on the HTV vehicle that, when checked on board the HTV, indicated the HTV would leave its designed departure corridor and thus it initiated an abort per joint safety requirements. No damage was done to the ISS. NASA has assessed a number of options to eliminate this interaction to mitigate risk of an abort on future vehicles and is implementing a modified SSRMS release approach to incorporate a delay in the start of initial SSRMS back away. Implementation is on schedule and includes refining visual cues for the crew to monitor the release as well as potentially adjusting SSRMS configuration parameters to provide a smooth separation between the SSRMS and the vehicle. NASA has assessed other free flyer vehicles (Dragon and Cygnus) and has implemented a corresponding approach to mitigate the concern.
Ø
Ø
15
Comparing Boeing 787 Li-Ion Battery to ISS Li-Ion
Ø January 7, Boston – post-landing, battery fire, see photos below January 16, Japan – emergency landing, pilots reported smoke odor, error battery messages Ø
Ø No fire, electrolyte leakage, battery case swollen Ø January 17, all 787s grounded pending investigation
Ø Boeing (Satellite Systems), GS Yuasa, NTSB, FAA Boeing (Houston) in communication with team and with NASA to understand the incidents Ø
Ø 787 battery is manufactured by Thales, using 8 GS Yuasa 65 Ah Li-ion cells ISS battery is manufactured by PWR, using 30 GS Yuasa 134 Ah Li-ion cells Ø
16
ISS Li-Ion Truss Batteries
ISS Li-Ion Battery Design 1 Li-Ion ORU will replace 2 series connected Ni-H2 ORUs 10-year design life (58,000 charge/discharge cycles) 134-Amp-hr (Ah) nameplate capacity, 15 kW-hours power Multiple layers of redundant controls and safeguards
Hardware and software / inside and outside the battery ORU Photovoltaic Control Application (PVCA) Battery Charge Discharge Unit (BCDU) Battery Interface Unit (BIU)
ORU Design Ø
Ø Ø Ø Ø
Ø Ø Ø Ø
Ø
High fidelity Engineering Model
Cell Selection Process Ø 2010 Risk Mitigation Study
Ø Evaluate candidate cells to meet ISS mission requirements Assessed for uniformity, design features, and manufacturing quality 7 Li-Ion cell designs were tested 2 remained viable candidates
Ø Ø Ø
Ø 2012 Cell selection Consideration Ø Supplier performance (lead time, current production, established baseline)
Management (preparation, participation, timeliness & accuracy) Technical (ability to maintain baseline material, meet specified requirements) Cost (total cost of product) GS Yuasa Lithium Power of Rosewell GA selected to provide cells
Ø Ø Ø Ø
Ø Each individual cell must pass rigorous acceptance testing before if can be used in an ISS battery
LSE 134 Cell
17
USOS System Enhancements
Ø Carbon Dioxide Removal Assembly (CDRA) “-4” Desiccant/Adsorbent Beds- Monitoring Ø Two new CDRA beds will be launched on SpX-2
New features include a redesigned heater core with significantly thicker Kapton insulation to reduce risk of short, and completely re-engineered attachment points to the wiring harness to reduce strain at the wiring interface New beds have been manufactured under clean-room conditions to reduce chance for built-in FOD Sheets for the heater core have been re-engineered to reduce sharp edges and weld points which were potential FOD sources from welding slag Beds incorporate new temperature sensors which have been changed from a thin-film sandwich type to a completely new helical wire-wound construction, significantly improving sensor survivability under repeated thermal cycles (similar to commercial applications in aircraft brakes) Shape of the desiccant and absorbent materials were changed to allow for more efficient packing on the ground and to potentially reduce dusting due to material abrasion when exposed to long term thermal/vacuum cycles on-orbit Housing of the bed was updated to accommodate the addition of captive fasteners and other features to allow the crew to partially disassemble the adsorbent bed on-orbit to remove the dust that accumulates from operation of the CDRA without having to return the beds to the ground for refurbishment
Ø
Ø
Ø
Ø
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USOS System Enhancements
Ø Continue replacement of legacy ISS avionics with Obsolescence Driven Avionics Replacement (ODAR) components Ø Integrated Communications Unit (ICU) ready for activation in early April - doubling the downlink
data rate (300 Mbps) and an eight-fold increase in the uplink data rate (25 Mbps) improved Payload Ethernet Hub Gateway (iPEHG) ready for activation in late May – tenfold increase in medium rate onboard data communications (100 Mbps) 2 flight ICUs and 4 iPEHGs are on-orbit; 3rd flight ICU planned for launch on ATV4 Installation is planned for April 2013
Ø
Ø Ø
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USOS System Enhancements
Ø The ELC Wireless system provides a COTS solution for external high data rate 802.11n wireless capability to payloads on the Express Logistic Carrier (ELC) The system consists of two separate segments Ø Ø US Lab
Ø COTS Wireless Access Points (WAP) placed inside the lab with external antennas to provide the core wireless capability
Ø Payloads/Users Ø Characterization of a wireless solution for the payloads/users to integrate and provide
piece parts to the developers Ø External Wireless users can connect using two methods:
Ø Use an IEEE 802.11n Network Interface Card in their device Ø The NIC can be integrated directly into the Payload. (e.g. a PCI card)
NASA can provide a USB NIC to a user that can be integrated into the Payload. Ø Ø Provide an IEEE 802.3 wired Ethernet interface and connect to Wireless Media Converter
Ø NASA is investigating providing a hardware (circuit card with wired Ethernet port and antenna out port) solution that will allow a Payload to use a standard wired Ethernet port and this hardware perform the wired to wireless conversion This hardware will be “smart” and require some configuration by the Payload in order to access the network Radiation testing on candidate hardware is being performed January 16 – 18
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USOS System Enhancements
Ø In an effort to increase the utilization of Commercial off the Shelf (COTS) hardware with limited or no modifications to support on-orbit operations, the ISS Program worked with commercial industry to develop a power inverter which converts the DC power generated from the ISS solar arrays to AC power just as you would find in your home. The provision of AC power allows ISS systems and payload developers to simplify and reduce the schedule and cost for the development, integration and delivery hardware into the ISS. The ISS power inverter (pictured below) comes in two models: 120Vdc-to120Vac and 28Vdc-to-120Vac respectively to support the primary power input voltages provided throughout the ISS (USOS and Russian Segments) and payload power interfaces. The 120Vdc-to120Vac power inverter provides power AC power provides: four (4) standard three prong AC power outlets and is capable of providing a total of 750W @ 60hz. The 28Vdc-to120Vac power inverter provides power AC power provides: four (4) standard three prong AC power outlets and is capable of providing a total of 400W @ 60hz.
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Ø Ø
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Ø Ø Ø
Ø
International Space Station SpaceX-2
SpX-2 Cargo
577 kg of pressurized launch cargo included the following:
95 kg of crew supplies and computer and EVA hardware 347 kg of utilization hardware including 2 GLACIERs and 5 double cold bags 135 kg of vehicle hardware including 2 Carbon Dioxide Removal Assembly (CDRA) desiccant absorbent beds
221 kg of unpressurized external cargo (first SpaceX flight with external cargo to ISS) included the following:
Two (2) Heat Rejection Subsystem Grapple Fixtures (HRSGF) (Grapple Bars)
1235 kg of pressurized return cargo plan included the following:
197 kg of crew supplies and computer and EVA hardware 576 kg of utilization hardware including 1 GLACIER and 5 double cold bags 462 kg of vehicle hardware
Status Successfully launched on 3/1 and berthed to ISS on 3/3 Grapple bars were successfully extracted on 3/6 Dragon unberthing/re-entry occurred on 3/26 with early destow cargo arrival at Long Beach on 3/27 and nominal return cargo arrival at McGregor scheduled for 4/2 Post-flight briefing to NASA occurred on 4/16
Dragon 4 (SpX-2) berthed to ISS on 3/3
Grapple bars in Dragon trunk ready for extraction
Photo Credits: NASA 22
Orbital Status
Ø 7K Hot Fire Test successfully completed on 2/22 Ø Post-test flame trench inspection yielded positive results; no
rework prior to Test Flight On-pad inspections and cleaning of Engines 2 & 3 completed Pad modifications on track for addition of a helium heat exchanger
Ø Ø
Ø Will improve the Liquid Nitrogen (LN2) subcooler’s ability to chill down helium entering the vehicle to meet launch vehicle requirements
Ø Test Flight status Ø Payload simulator mated on 2/20
Launch planned for NET 4/20 Ø Ø Demo Launch status
Ø Pressurized Cargo Module (PCM) Initial Cargo Load occurred on 3/22 PCM-to-SM mate occurred on 4/1 – 4/2 Final Flight Software regression testing conducted on 3/19 and Joint Test 4 Software Stage Verification conducted on 4/2 – 4/5 Joint Multi-Segment Training (JMST) #10 (long rendezvous) simulation was successfully conducted on 3/21 NASA’s Vehicle Assessment Review (VAR) is planned on 5/2 Cargo upmass allocation is 704 kg
Ø Ø
Ø
Ø Ø
Ø Ascent manifest consists of crew provisions, food, laptops, and other non-critical hardware (no utilization)
Successful 7K Hot Fire Test
Test Flight Fairing and Payload Simulator
Photo Credits: OSC
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International Space Station ATV4
ATV4: Albert Einstein Ø Launch
Ø The launch date for ATV4 was moved out due to a connector inside of the pressurized module requiring a repair as well as a Digital Signal Processing Unit (DSPU) being removed and replaced
Ø Cargo Ø Nominal cargo load is complete
Late load is planned at L-3 weeks Manifest (in kg): ~2200 prop for ISS use, 860 prop for transfer, 100 (air and O2), 570 water, and ~2700 packed dry cargo
Ø Ø
Ø Status Ø ATV target on Service Module has contamination
which has caused pitch/yaw noise on all ATVs. Noise has been worsening on each flight. ESA management has decided to have RSCE swap out target during 4/19 Russian EVA ATV2 and ATV3 cabin fan failure investigations largely complete with no clear identification of root cause. Spare fan on board ISS will be installed if ATV4 fan should fail. Most ATV operations may continue without operational ATV cabin fan (covered by a Flight Rule) Stage Operations Readiness Review is planned for 5/13
Ø
Ø Pressurized module for Albert Einstein (ATV4) on production line
Photo Credits: ESA 24
Ø Ø ~
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Ø Ø
Ø Ø Ø Ø
Ø Ø
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International Space Station HTV4
HTV4 Cargo – (Manifest Requests (MRs) pending)
3144 kg currently manifested for ISS 2257 kg of pressurized cargo, including crew supplies and computer resources (582 kg), water bags and flight support equipment (571 kg), vehicle hardware (676 kg), utilization hardware (357 kg), EVA supplies (71 kg), and 887 kg of unpressurized cargo
External cargo includes: Space Test Program – Houston 4 (STP-H4) Main Bus Switching Unit (MBSU) Utility Transfer Assembly (UTA) For disposal: STP-H3
Status Launch date moved due to a potential Earth Sensor Assembly(ESA) issue found during acceptance test on an HTV7 unit. STP-H4, UTA, and MBSU have been integrated onto the Exposed Pallet. For MBSU/UTA IAs, this was the first time JAXA performed all physical integration at TNSC without NASA touch labor (observers only); STP-H4 personnel performed offline testing and checkouts prior to turnover to JAXA; Processing of water and filling of the Contingency Water Containers – Iodine (CWCI) began in early March; leak subsequently discovered on one bag and replacement bags have been shipped. NASA is flying 24 CWCIs
HTV launch from Tanegashima Space
Center
HTV on approach to ISS Photo Credits: JAXA/NASA 25
ISS Top Program Risk Matrix Post April 10, 2013 PRAB
Risks (L x C) continued Score: 2 x 4
L I K E L I H O O D
p
pp
p p p
p
p
p
p
p
p
p
p
p
p
6368 - Development of ISS On-Orbit Nitrogen and Oxygen Recharge Capability - (OG) - (C,S,T,Sa)
Score: 3 x 2 p 6393 - Channel 2B PVTCS Ammonia Leak
Increasing - (OB) - (C,S,T,Sa) Score: 2 x 2 p 6347 - Temporary Urine and Brine Stowage
System Catastrophic leak of a Tox-2 Fluid - (OB) - (C,S,T,Sa)
6032 - On-Orbit Stowage Short-Fall (Pressurized Volume) - (OC) - (T,Sa)
p
Corrective/Preventative Actions None
Watch Items None
Continual Improvement None
5 2 1
4 2 3
3 1 3 1 3
2 2 1
1
1 2 3 4 5 CONSEQUENCE
Low Medium High
C – Cost S – T – Schedule Technical Sa – Safety
p – Top Program Risk (TPR)
Removed: 6198 - ODAR/ICU, 6234 - Institutional Gaps, and 6407 - SpX Engine Anomaly
Risks (L x C) Score: 5 x 5
6352 - Overlap in Commercial Crew & Soyuz Launch Services - (OH) - (C,S,T,Sa)
Score: 5 x 4 6370 - ISS Pension Harmonization - (OH) - (C) 6344 - ISS Operations Budget Reduction - (OH) - (C)
Score: 4 x 4 6399 - ISS Budget and Schedule - (OH) - (C,S,T) 6372 - Full ISS Utilization - (OZ) - (S) 6169 - Visual Impairment / Intracranial Pressure - (SA) -
(C,S,T,Sa)
Score: 3 x 5 6420 - NDS and IDA Qualification Schedule - (OG) -
(C,S,T,Sa) 5688 - ISS Solar Array Management Operations Controls
and Constraints - (OM) - (C,S,T,Sa) 2810 - Russian Segment (RS) capability to provide
adequate MM/OD protection - (OM) - (C,S,T,Sa)
Score: 3 x 4 6408 - FGB Sustaining Contract and FGB spares plan
post 2016 undefined - (OB) - (C,S,T,Sa)
Score: 4 x 3 6413 - ELC ExPCA Low Voltage Power Supply (LVPS)
Board Design Flaw - (OB) - (C,S,T,Sa) 5269 - The Big 13 Contingency EVA's - (OB) - (S,T,Sa)
Score: 3 x 3 6402 - SpaceX Dragon splash down - water intrusion /
power outage - (ON) - (S,T) 6277 - Loss of utilization flexibility based on CRS
capabilities - (OZ) - (C,T) 5184 - USOS Cargo Resupply Services (CRS) Upmass
Shortfall - 2010 through 2016 - (ON) - (C,S,T,Sa)
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ISS Program Focus
Tact icalMaintain/increase crew t ime & resources for ut ilizat ionCont inue preparat ions for 1 year IncrementFY13 budget postureExecute SpaceX-3 mission & complete Orbital test anddemonstrat ion missionsATV 4 launchHTV 4 launchBetter ut ilize on-orbit stowage to improve crew t imeef f iciencyCommercial Crew Integrat ion
StrategicMaximum ut ilizat ion of ISS as a Nat ional LabTechnology development and demonstrat ionTest bed for Explorat ion and extension of ISS capabilit ies foruse in deep spaceCrew transportat ion planTechnical analysis & planning of ISS life extensionsionBudget formulat ion to address challenges over the budgethorizon
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