1 NASA: OC4/John Coggeshall For current baseline refer to MAPI: OP/Scott Paul SSP 54100 Multi-Increment Chart Updated: April 3rd, 2013 Planning Document (MIPD) ISS Flight Plan SSCN/CR: 13681A + Tact. Mods (In-Work) 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 In Inc 35 Inc 36 Inc 37 Inc 38 Inc 39 Inc 40 Inc 41 Inc 42 c (32S) R P. Vinogradov (CDR-36) 167 days (34S) R O. Kotov (CDR-38) 168 days (36S) N S. Swanson (CDR-40) 174 days (38S) N B. Wilmore (CDR-42) 167 days (40S) N K. (32S) R Misurkin 167 days (34S) R S. Ryazanskiy 168 days (36S) R A. Skvortsov 174 days (38S) R Y. Serova 167 days (40S) R O. (32S) N Cassidy 167 days (34S) N M. Hopkins 168 days (36S) R O. Artemyev 174 days (38S) R A. Samokutyayev 167 days (40S) R E. C C. Hadfield (33S) R F. Yurchikhin (CDR-37) 166 days J K. Wakata (CDR-39) 188 days (37S) R M. Suraev (CDR-41) 173 days (39S) N T. Virts (CDR-43) (CDR-35) R R. 146Romanenko days (33S) N K. Nyberg 166 days N R. Mastracchio 188 days (37S) N R. Wiseman 173 days (39S) 166 days E S. Cristoforetti 166 146 days N T. Marshburn (33S) A L. Parmitano 166 days R M. Tyurin 188 days (37S) E A. Gerst 173 days (39S) days R A. Shkaplerov 166 146 days days
05/25 06/15 07/23 08/15 09/17 10/22 11/13 12/23 Soyuz Lit Landing DO01: DO02: 05/27 07/25 09/19 11/15 ICU SM 8.07 X2R12.1 X2R13 Stage S/W 4/2, 4/11 9/9u/r 3/17 9/15 R-32 R-33 U-21, 22u/r R-34, 35 R-36 R-37 R-38, 39 R-40,41,42 R-43 R-44 R-45,46,47 R-48 Stage EVAs 4/19 ~6/26 Jul Aug Nov 9 Dec Jan Feb Apr Jun Aug Jan 3/15 3/29 9/11 9/27 1/12 2/7 3/25 3/28 7/20 7/26 12/30 2/4 MRM2 167 / 167 168 / 166 174 / 172
(SM 32S 34S 36S 54P 38S 56P 58P Zenith) #3-7 (Beta) 5/14 5/30 11/10 11/15 5/14 5/30 11/17 12/3
Port Utilization MRM1 146 / 144 166 / 164 188 / 188 173 / 171 166 / 164 (FGB 33S 35S 39S 41S Nadir) 7/21 7/26 12/18 3/12 4/30 6/23 9/16 10/2 DC-1/ 167 / 165 MLM/ RS Node 50P 52P 3R (MLM) 55P 6R (RS-Node) 40S 3-7 12/20 3-81 # ATV4 6/26 # 4/15 4/26 6/11 6/16 -18 6/26 – 7/25 8/15, 17-18 11/7 11/23 4/9 4/20 10/9 10/24 6/15 #3-76 10/31 180 / 172 SM-Aft 148 / 138 49P 51P 37S 53P ATV5 57P ATV4 Node-2 Zenith 12/11 1/10 4/8 5/8 3-7 (beta) 3-73 30 d 30 d # #3-80 # #3-7 (Beta) Orb-2 Orb-3 3-75 3/3 3/25 6/10 7/5 8/9 9/8 9/15 10/15 # 7/6 8/5 8/10 9/9 10/6 11/5 12/7 1/6 1/18 2/17 25 d 11/13 12/13 3-75 4/8 5/8 Node-2 22 d 30 d 30 d 30 d # 30 d 30 d 30 d 30 d 30 d 30 d Nadir SpX-2 Orb-D1 HTV4 Orb-1 SpX-3 SpX-4 HTV5 SpX-5 Orb-4 SpX-6 Orb-5 N2 Fwd
Solar Beta >60 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 External Cargo SpX-3: HDEV, OPALS HTV5: CALET, CATS SpX-6: SAGE Hexapod, SAGE NVP, MUSES #3-7 (TDRSS) HTV4: MBSU, UTA, STP-H4 SpX-4: RapidScat SpX-5: CREAM Orb-TF 4/17
SpX-2 ATV4 Orb-D1 HTV4 Orb-1 SpX-3 Orb-2 Orb-3 SpX-4 ATV5 HTV5 SpX-5 Orb-4 SpX-6 Orb-5 Launch 3/1 6/5 6/5 NET 8/4 9/12 11/11 12/8 4/5 4/6 4/12 7/1 8/8 10/3 12/5 1/15 N°708 N°419 N°709 N°420 N°710 N°711 N°421 MLM N°422 N°712 N°423 N°713 RS-Node N°424 N°714 N°425 N°715 N°426 Schedule TMA-08M M-19M TMA-09M M-20M TMA-10M TMA-11M M-21M M-22M TMA-12M M-23M TMA-13M M-24M TMA-14M M-25M TMA-15M M-26M
6R 34S 51P 35S 52P 36S 37S 53P 3R 54P 38S 55P 39S 56P 40S 57P 41S 58P 3/28 4/24 5/28 7/24 9/25 11/7 11/21 12/11 2/5 3/26 4/28 5/28 6/24 7/24 9/30 10/22 12/1 2/2 #3-8 #3-8 #3-8 #3-8 #3-8 #3-8 #3-8 #3-8 #3-8 #3-8 4-Orbit Rendezvous
Ø 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. Ø From the USOS perspective, docking timeline is essentially identical for either rendezvous Ø System configurations (powerdowns, array positioning, attitude control handover) occur at same time relative to docking and are identical to any other Soyuz Ø No changes to joint Flight Rules or USOS procedures for the 4-orbit rendezvous Ø U.S. and Russian flight control and engineering teams have performed standard analysis for both 4-orbit and 34-orbit dockings Ø 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 Ø Crew fatigue and health management Ø US and RS doctors approved a sleep shifting profile to align with launch / docking activities. Ø Crew activities post ingress were limited to the Safety briefing. 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. Ø MAGs were approved and available to all crew members Ø Crew able to loosen straps on-orbit to allow stretching and mitigate join pain. 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 36 Expedition 35 Pavel Vinogradov (CDR) Chris Hadfield (CDR) Alexander Misurkin Roman Romanenko Chris Cassidy Tom Marshburn (34S-Soyuz TMA-08M) (33S-Soyuz TMA-07M) 5
FPIP SSCNs 13706/13681A IDRD Rev A CR13583
Inc 34 Increment 35 Increment 36 Inc 37 Mar-2013 Apr-2013 May-2013 Jun-2013 Jul-2013 Aug-2013 Sep- 2013 3/15 MRM2 32S Undock 29- Mar 34S 11-Sept MRM1 33S 14- May 30-May 35S DC-1 50P 23- 26-April 51P 21-July 26-July 52P Apr SM Aft 49P 15- 15–June ATV4 Apr N2 Zenith 15 - N2 Nadir Sept 9-Aug 8-Sept 25-Mar Berth 17- 5-July Berth HTV4 Unberth SpX-2 Unberth Orb-D1 June Unberth Orb-1 Berth Stage 35-3 Stage 35-6 Stage 36-3 Stage 34-6 (14 Days) (45 Days) (16 Days) Stage 36-6 (104 Days)
3/15 RS #32 5/14 5/30 RS #33 USOS 36 - #1 RS #34 RS #35 3/29 April 19, 2013 June ‘13 & 2 Aug‘13 Aug‘13 9/11 32S Undock 34S Dock 33S Undock 35S Dock July 2013 34S Undock CDR K. Ford E35 FE-1 /E36 CDR - P. Vinogradov (Inc 35 – 46 days, Inc 36 – 120 days) FE-1 O. Novitskiy E35/E36 FE-2 – A. Misurkin (Inc 35 – 46 days, Inc 36 – 120 days) FE-2 E. Tarelkin E35/E36 FE-3 – C. Cassidy (Inc 35 – 46 days, Inc 36 – 120 days) E 35 CDR – C. Hadfield (Inc 35 60 days) E 36 FE-4 – F. Yurchikhin (Inc 36 – 104 days) E 35 FE-4 – R. Romanenko (Inc 35 60 days) E 36 FE-5 – L. Parmitano (Inc 36 – 104 days) E 35 FE-6 – T. Marshburn (Inc 35 60 days) E 36 FE-6 – K. Nyberg (Inc 36 – 104 days) Stage 35-3 Stage 35-6 Stage 36-3 Stage 36-6 33 34 35 • • Soyuz Soyuz Soyuz U liza on More than 75 inves ga ons during More than 75 inves ga ons during Stages 36-3 and 36-6 Stage 35-3 and 35-6 • New Inves ga ons: Microbiome, ICE-GA, Diapason, STP-H4, RINGS, Crew Crew Crew Inc Ave 35 • New Inves ga ons: BP Reg, Car lage, Ocular Health, Skin-B, Space PUP, and Asian Seed. hrs / wk FASES, ICE-GA, and UVP-2R
• RS EVA #32: • RS EVA #33: R&R FGB thermal regulator panel, photo Obstanovka exp. external surfaces of the RS MLI, remove the Foton- Setup, ATV reflector Gamma from Molniya-Gamma experiment Vinogradov R&R • USOS EVA #36-1: MLM Pwr cable, SGTRC-2 R&R, Grapple • R&O: Install ICU, Bar, MISSE8 & ORMatE retrieval, Z1 Jumper (1 of 2) EVA, iPEHG, High Defini on • USOS EVA #36-2: RGB V-Guides, MLM Ethernet cable, Z1 Misurkin Cameras Resupply Jumper, R&R JEF Fwd Cam, FGB PDGF 1553 Romanenko Hadfield & • RS EVA #34: Route power from FGB to MRM2, route Ou i ng Ethernet cable for MRM2 • RS EVA #35: Set up the portable worksta on, the two- Nyberg Parmitano Yurchikhin Yurchikhin Parmitano Nyberg Cassidy Cassidy
axial targe ng pla orm, and the medium resolu on Marshburn
camera (MRC) on the Plane IV portable worksta on • R&O: Install HTV4 H/W: JEM LAN, JEM Environmental Monitor Equip, U lity Bonding Point, Cooler Box 6 ISS Expedition 35 Mission Objectives March 2013 – May 2013
Ø Perform an average of 35 hrs/week for Ø Support visiting vehicle traffic including: payload investigations Ø SpaceX-2 unberthing, planned March 25th Ø 34 Soyuz docking, planned March 30th, first Soyuz to Ø FASES Inves gates the emulsion stability in rela on to the perform a 4-orbit rendezvous profile. physical-chemistry of droplet interfaces to obtain a modeling of Ø 49 Progress undocking, planned April 15th emulsion dynamics to be transferred to industrial applica ons Ø RS EVA #32, planned April 19th on Earth. Ø 50 Progress undocking, planned April 23rd Ø 51 Progress docking, planned April 26th Ø BP Reg Will test the efficacy of an in-flight manipula on of Ø ATV-4 docking, planned May 1st arterial blood pressure (BP) as an indicator of post-flight response to a brief stand test. Ø Installation of Ku Comm Unit Ø Will increase hi rate Ku downlink from 150 Mbps to Ø Microbiome This study will carry out a thorough 300 Mbps, adds S/G3 and S/G4 (audio), adds two evalua on of how long-term space travel impacts the human more channels of downlink video, reduces video microbiome and ul mately human health, and it will form the bandwidth consumption (using new encoder basis for further studies towards the design of therapies to algorithm), provides increased solid state recording mi gate any microbiome changes or related health issues of payload and video data. found as a result of this project. Ø Ocular Health Collect evidence to characterize the risk and define the visual changes and central nervous system (CNS) changes observed during a six month exposure to microgravity including pos light me course for recovery to baseline. Ø Tritel Characterizes the radia on environment within the Columbus module of the ISS with high accuracy. It uses a Space-X Dragon combina on of three different detector types measuring the capsule approaching radia on amount, direc on and history to determine absorbed and berthed to the ISS dose and dose equivalent from solar and galac c radia on.
7 Increment 33_34 Utilization Crew Time
OOS Planned USOS Executed 35 Hrs/Wk Avg Requirement OOS Planned Cumula ve USOS Cumula ve Executed 80 1000.00
900.00 70 800.00 60 700.00 50 600.00
40 500.00
400.00 30 300.00 Weekly Crew Time (Hours) 20 200.00 10 100.00 Cumula ve Scheduled Crew Time (Hours) 0 0.00 0 1 2 3 4 5 6 7 8 9 11 15 17 18 19 21 25 10 12 13 14 16 20 22 23 24 26
Inc 36 Orb-D1 SpX-1 (3/3/13 – Inc 35) ATV3 US EVA #20 (11/1/12) *CONT (12/17/12 – 12/29/12) SpX-2 (1/20/13 – 2/19/13) (Undock on 9/25/12) (10/11/12 – 10/28/12) (Undock on 9/28/12) (10/10/12 – 10/28/12) Executed through Increment Wk (WLP week) 25 = 25.0 of 24.8 work weeks 100.81 % through the Increment OC/OZ USOS IDRD & OOS Allocation: 868.0 hours reconciliation is Additional USOS Allocation for Stage 34-6: 928.0 hours (Additional 60 hours) complete through Date Color USOS Actuals: 938.73 hours Week 25 with the Key: Completed 101.2 % through updated Stage 34-6 Allocation exception of ESA 33-34 Final time. OOS 108.1 % through IDRD and OOS Allocation FPIP Plan Total USOS Average Per Work Week: 37.55 hours/work week Pre-Decisional, For Internal Use Only Voluntary Science Totals to Date: 5.08 hours (Not included in the above totals or graph) Increment 35_36 Utilization Crew Time
OOS Planned USOS Executed 35 Hrs/Wk Avg Requirement
OOS Planned Cumula ve USOS Cumula ve Executed 70 1000.00
900.00 60 800.00
50 700.00
600.00 40 500.00 30 400.00 Weekly Crew Time (Hours) 20 300.00 200.00 10 100.00 Cumula ve Scheduled Crew Time (Hours) 0 0.00 2 3 6 1 4 5 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26
3-Crew 6- Crew 3-Crew 6-Crew Increment 35 Increment 36 March April May June July August Sept (Dock on 6/15/13) (8/9/13 – 9/8/13) SpX-2 HTV ATV4 (Berth on (Unberth on 3/24/13) (Berth on 5/8/13) (7/20/134 – 8/19/13) (Dock on 5/1/13) 6/10/13) (Unberth on 3/25/13) Orb-D1 Below the line US EVAUS EVA Executed through Increment Wk (WLP week) 2 = 2.0 of 24.4 work weeks 8.20 % through the Increment OC/OZ USOS IDRD Allocation: 875 hours Date Color reconciliation OOS USOS Planned Total: 876.5 hours Key: completed as of USOS Actuals: 81.41 hours Completed Week 2. 35-36 Final 9.3 % through IDRD Allocation OOS 9.3 % through OOS Planned Total FPIP Plan Total USOS Average Per Work Week: 40.71 hours/work week Pre-Decisional, For Internal Use Only 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 Inves ga ons for 35/36 : 140 • 82 NASA/U.S.-led inves ga ons • Over 400 Inves gators • 58 Interna onal-led inves ga ons represented • 30 new USOS inves ga ons • Over 500 scien fic results – 1 CSA publica ons (Exp 0 – present) – 4 ESA Roscosmos data s ll in work – 7 JAXA – 18 NASA/U.S. ISS Research Disciplines by Partner Agency Increments 35/36 100% 90% 80% Biology and Biotechnology 70% 60% Earth and Space Science 50% Educa onal and Cultural Ac vi es 40% Human Research 30% Physical Science 20% Technology 10% TBD 0% CSA ESA JAXA NASA/US 9 20 29 82 10 Number of Inves ga ons Expedi on 0-32: 1549* *USOS + Roscosmos 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, Date to Reserve Level Date to zero supplies Date to Reserve Level Date to zero supplies ISS system status
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) August 24, 2013 October 16, 2013 October 12, 2013 December 4, 2013 (2) (5) O if Elektron supporting 3 crew 2 July 5, 2013 December 2, 2013 July 18, 2013 December 15, 2013 & no OGA (2) (6) O if neither Elektron or OGA (2) 2 May 1, 2013 July 6, 2013 May 7, 2013 July 13, 2013 (6)
LiOH (7) ~4 Days ~18 Days ~4 Days ~18 Days (CDRAs and Vozdukh off)
(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 USOS System Challenges
Ø Loss of Columbus Water Pump Assembly (WPA2) - Monitoring Ø 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.
Ø Increased N3 Common Cabin Air Assemblies (CCAA) Indications - Workaround Ø Water carryover events due to degraded heat exchanger (HX) in N3 CCAA. No spare CCAA HXs on orbit; one targeted for manifesting on HTV5. Ø 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 Ø 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 Ø Although check valves operated nominally upon entry into ISS ellipsoid, sufficient blowdown was available should an abort be required Ø Check valve operated nominally for departure and re-entry
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. Ø 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. Ø NASA has assessed other free flyer vehicles (Dragon and Cygnus) and has implemented a corresponding approach to mitigate the concern. 15 Comparing Boeing 787 Li-Ion Battery to ISS Li-Ion
Ø January 7, Boston – post-landing, battery fire, see photos below Ø January 16, Japan – emergency landing, pilots reported smoke odor, error battery messages Ø No fire, electrolyte leakage, battery case swollen Ø January 17, all 787s grounded pending investigation Ø Boeing (Satellite Systems), GS Yuasa, NTSB, FAA Ø Boeing (Houston) in communication with team and with NASA to understand the incidents Ø 787 battery is manufactured by Thales, using 8 GS Yuasa 65 Ah Li-ion cells Ø ISS battery is manufactured by PWR, using 30 GS Yuasa 134 Ah Li-ion cells
16 ISS Li-Ion Truss Batteries
ORU Design Ø ISS Li-Ion Battery Design Ø 1 Li-Ion ORU will replace 2 series connected Ni-H2 ORUs Ø 10-year design life (58,000 charge/discharge cycles) Ø 134-Amp-hr (Ah) nameplate capacity, 15 kW-hours power Ø Multiple layers of redundant controls and safeguards Ø Hardware and software / inside and outside the battery ORU Ø Photovoltaic Control Application (PVCA) Ø Battery Charge Discharge Unit (BCDU) High fidelity Engineering Model Ø Battery Interface Unit (BIU) Ø Cell Selection Process Ø 2010 Risk Mitigation Study Ø Evaluate candidate cells to meet ISS mission requirements Ø Assessed for uniformity, design features, and manufacturing quality Ø 7 Li-Ion cell designs were tested Ø 2 remained viable candidates LSE 134 Cell Ø 2012 Cell selection Consideration Ø Supplier performance (lead time, current production, established baseline) Ø Management (preparation, participation, timeliness & accuracy) Ø Technical (ability to maintain baseline material, meet specified requirements) Ø Cost (total cost of product) Ø GS Yuasa Lithium Power of Rosewell GA selected to provide cells Ø Each individual cell must pass rigorous acceptance testing before if can be used in an ISS battery
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 Ø 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 Ø New beds have been manufactured under clean-room conditions to reduce chance for built-in FOD Ø Sheets for the heater core have been re-engineered to reduce sharp edges and weld points which were potential FOD sources from welding slag Ø 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) Ø 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 Ø 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
18 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) Ø improved Payload Ethernet Hub Gateway (iPEHG) ready for activation in late May – tenfold increase in medium rate onboard data communications (100 Mbps) Ø 2 flight ICUs and 4 iPEHGs are on-orbit; 3rd flight ICU planned for launch on ATV4 Ø Installation is planned for April 2013
19 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) Ø The system consists of two separate segments 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) Ø NASA can provide a USB NIC to a user that can be integrated into the Payload. 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 Ø This hardware will be “smart” and require some configuration by the Payload in order to access the network Ø Radiation testing on candidate hardware is being performed January 16 – 18
20 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. Ø 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. Ø 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. Ø 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. Ø 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.
21 International Space Station SpaceX-2
SpX-2 Ø Cargo Ø 577 kg of pressurized launch cargo included the following: Ø 95 kg of crew supplies and computer and EVA hardware Ø 347 kg of utilization hardware including 2 GLACIERs and 5 double cold bags Ø 135 kg of vehicle hardware including 2 Carbon Dioxide Removal Assembly (CDRA) desiccant absorbent beds Ø 221 kg of unpressurized external cargo (first SpaceX flight with external cargo to ISS) included the following: Dragon 4 (SpX-2) berthed to ISS on Ø Two (2) Heat Rejection Subsystem Grapple Fixtures (HRSGF) (Grapple Bars) 3/3 Ø 1235 kg of pressurized return cargo plan included the following: Ø 197 kg of crew supplies and computer and EVA hardware Ø 576 kg of utilization hardware including 1 GLACIER and 5 double cold bags Ø 462 kg of vehicle hardware Ø Status Ø Successfully launched on 3/1 and berthed to ISS on 3/3 Ø Grapple bars were successfully extracted on 3/6 Ø 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 Grapple bars in Dragon trunk Ø Post-flight briefing to NASA occurred on 4/16 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 Ø On-pad inspections and cleaning of Engines 2 & 3 completed Ø Pad modifications on track for addition of a helium heat exchanger 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 Successful 7K Hot Fire Test Ø Launch planned for NET 4/20 Ø Demo Launch status Ø Pressurized Cargo Module (PCM) Initial Cargo Load occurred on 3/22 Ø PCM-to-SM mate occurred on 4/1 – 4/2 Ø Final Flight Software regression testing conducted on 3/19 and Joint Test 4 Software Stage Verification conducted on 4/2 – 4/5 Ø Joint Multi-Segment Training (JMST) #10 (long rendezvous) simulation was successfully conducted on 3/21 Ø NASA’s Vehicle Assessment Review (VAR) is planned on 5/2 Ø Cargo upmass allocation is 704 kg Ø Ascent manifest consists of crew provisions, food, Test Flight Fairing and Payload laptops, and other non-critical hardware (no utilization) Simulator
Photo Credits: OSC 23 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 Ø Late load is planned at L-3 weeks Ø Manifest (in kg): ~2200 prop for ISS use, 860 prop for transfer, 100 (air and O2), 570 water, and ~2700 packed dry cargo 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 Ø 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) Ø Stage Operations Readiness Review is planned for 5/13 Pressurized module for Albert Einstein (ATV4) on production line
Photo Credits: ESA 24 International Space Station HTV4
HTV4 Ø Cargo – (Manifest Requests (MRs) pending) Ø ~3144 kg currently manifested for ISS Ø 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 Ø 887 kg of unpressurized cargo Ø External cargo includes: Ø Space Test Program – Houston 4 (STP-H4) Ø Main Bus Switching Unit (MBSU) Ø Utility Transfer Assembly (UTA) Ø For disposal: STP-H3 HTV launch from Ø Status Tanegashima Space Ø Launch date moved due to a potential Earth Sensor Center Assembly(ESA) issue found during acceptance test on an HTV7 unit. Ø 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; Ø 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 on approach to ISS Photo Credits: JAXA/NASA 25 ISS Top Program Risk Matrix Post April 10, 2013 PRAB
Risks (L x C) Risks (L x C) continued Score: 5 x 5 Score: 2 x 4 5 2 1 p 6352 - Overlap in Commercial Crew & Soyuz Launch p 6368 - Development of ISS On-Orbit Nitrogen and L Services - (OH) - (C,S,T,Sa) Oxygen Recharge Capability - (OG) - (C,S,T,Sa) I Score: 5 x 4 K 4 2 3 p 6370 - ISS Pension Harmonization - (OH) - (C) Score: 3 x 2 p 6344 - ISS Operations Budget Reduction - (OH) - (C) p 6393 - Channel 2B PVTCS Ammonia Leak E Increasing - (OB) - (C,S,T,Sa) L Score: 4 x 4 3 1 3 1 3 p 6399 - ISS Budget and Schedule - (OH) - (C,S,T) Score: 2 x 2 I p 6372 - Full ISS Utilization - (OZ) - (S) p 6347 - Temporary Urine and Brine Stowage H p 6169 - Visual Impairment / Intracranial Pressure - (SA) - System Catastrophic leak of a Tox-2 Fluid - (C,S,T,Sa) (OB) - (C,S,T,Sa) O 2 2 1 p 6032 - On-Orbit Stowage Short-Fall (Pressurized O Score: 3 x 5 Volume) - (OC) - (T,Sa) p 6420 - NDS and IDA Qualification Schedule - (OG) - D (C,S,T,Sa) 1 p 5688 - ISS Solar Array Management Operations Controls and Constraints - (OM) - (C,S,T,Sa) p 2810 - Russian Segment (RS) capability to provide adequate MM/OD protection - (OM) - (C,S,T,Sa) 1 2 3 4 5 Score: 3 x 4 CONSEQUENCE p 6408 - FGB Sustaining Contract and FGB spares plan post 2016 undefined - (OB) - (C,S,T,Sa) Corrective/Preventative Actions Low Medium High Score: 4 x 3 None S – T – p 6413 - ELC ExPCA Low Voltage Power Supply (LVPS) C – Cost Sa – Safety Schedule Technical Board Design Flaw - (OB) - (C,S,T,Sa) Watch Items p 5269 - The Big 13 Contingency EVA's - (OB) - (S,T,Sa) p – Top Program Risk (TPR) None Score: 3 x 3 Continual Improvement Removed: 6198 - ODAR/ICU, 6234 - Institutional p 6402 - SpaceX Dragon splash down - water intrusion / Gaps, and 6407 - SpX Engine Anomaly power outage - (ON) - (S,T) None p 6277 - Loss of utilization flexibility based on CRS capabilities - (OZ) - (C,T) p 5184 - USOS Cargo Resupply Services (CRS) Upmass Shortfall - 2010 through 2016 - (ON) - (C,S,T,Sa)
26 ISS Program Focus
Tac cal Ø Maintain/increase crew me & resources for u liza on Ø Con nue prepara ons for 1 year Increment Ø FY13 budget posture Ø Execute SpaceX-3 mission & complete Orbital test and demonstra on missions Ø ATV 4 launch Ø HTV 4 launch Ø Be er u lize on-orbit stowage to improve crew me efficiency Ø Commercial Crew Integra on
Strategic Ø Maximum u liza on of ISS as a Na onal Lab Ø Technology development and demonstra on Ø Test bed for Explora on and extension of ISS capabili es for use in deep space Ø Crew transporta on plan Ø Technical analysis & planning of ISS life extension Ø Budget formula on to address challenges over the budget horizon
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