international space station national research...

International Space Station

National Research Council

April 2013

Michael T. Suffredini

Manager, ISS Program Office 1

Mass = 902,000 lbs

Truss Length = 358 ft

Altitude = 224 nautical miles

Living space = 32,333 ft3

Velocity = 17,500 mph

Solar array surface area = 38,400 ft2

(0.88 acre) generating 84 kW

Assembly flights = 41

Spacewalks = 161 (1015 hours)

Crew members = 205 different people

from 15 countries Continuous human presence

since November 2000

ISS Facts and Figures

ISS Configuration

3

ISS TRANSPORTATION SYSTEMS

Ariane/

ATV Proton

Soyuz /

Progress

H-IIB/

HTV

Falcon 9/

Dragon

Antares/

Cygnus Commercial

Crew Potential

Candidates

4

NASA: OC4/John Coggeshall

MAPI: OP/Scott Paul

Chart Updated: April 3rd, 2013

SSCN/CR: 13681A + Tact. Mods (In-Work)

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

Po

rt Utiliz

atio

n

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

N°708

TMA-08M

5/28 35S

N°709

TMA-09M

9/25 36S

N°710

TMA-10M

11/7

37S

N°711

TMA-11M

3/26 38S

N°712

TMA-12M

5/28 39S

N°713

TMA-13M

9/30 40S

N°714

TMA-14M

12/1 41S

N°715

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

N°419

M-19M

7/24 52P

N°420

M-20M

11/21

53P

N°421

M-21M

2/5 54P

N°422

M-22M

4/28 55P

N°423

M-23M

7/24 56P

N°424

M-24M

10/22 57P

N°425

M-25M

2/2 58P

N°426

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

In 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

(32S)

(32S)

(32S)

C C. Hadfield (33S)

R R. Romanenko (33S)

N T. Marshburn (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)

E S. Cristoforetti 166

R A. Shkaplerov 166

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 6/26 – 7/25 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

Flight Planning Integration Panel (FPIP)

Executed through Increment Wk (WLP Week) 3 = 3 of 24.4 work weeks (12.30% through Increment)

USOS IDRD Allocation: 875 hours

OOS USOS Planned Total: 876.5 hours

USOS Actuals: 120.17 hours

13.73% through IDRD Allocation

13.71% through OOS Planned Total

Total USOS Average Per Work Week: 40.06 hours/work week

Voluntary Science Totals to Date 0 hours (Not included in the above totals or graph)

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 3/26/13)

(Berth on 5/8/13) Below the line (Dock on 5/1/13)

HTV4 (7/20/13 – 8/19/13)

Date Color Key:

Completed

35-36 Final OOS

FPIP Plan

OC/OZ reconciliation completed as of Week 3.

(Berth on 6/10/13)

(Dock on 6/15/13) (8/9/13 – 9/8/13)

0

100

200

300

400

500

600

700

800

900

1000

0

10

20

30

40

50

60

70

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

Cu

mu

lati

ve S

che

du

led

Cre

w T

ime

(H

ou

rs)

We

ekl

y C

rew

Tim

e H

ou

rs

Inc 35 - 36 Utilization Crew Time

USOS Executed OOS Planned USOS Cumulative Executed OOS Planned Cumulative

WLP 2 contains 35 minutes of ESA Utilization that has not been agreed

upon.

6

-

5

10

15

Crew Supplies, Water, Gas Maintenance / EVA Utilization Baseline

Baseline Capability CSOC Capability CRS Capability

PPBE-15: Capability vs. Demand

and Flight Rate – Pressurized

*Overguide request – will submit 2 year Soyuz overlap

Notes:

-Demo flights are not included in the flight rate table.

- Flight rate supports 4th crewmember beginning in Nov. 17

MT

2013 2014 2015 2016 2017 2018 2019 2020

US Crew Vehicle 2 2 2

USOS Progress 0.7 MT 0.3 MT 0.3 MT 0.3 MT 0.3MT 0.3* MT 0.3* MT

USOS Soyuz 2 2 2 2 2 2* 2*

RS Progress 4 4 4 4 4 4 4 4

RS Soyuz 2 2 2 2 2 2 2 2

ATV 1 1 0 0 0 0 0 0

HTV 1 1 1 1 1** 1** 1**

SpaceX 2 3 4 3

Orbital 2 2 2 2

CRS Future Flights 1 4 6 6 6

676 1,840 (2,849) 599 573 (892) (916) (1,017)

7.6 Mt 11.7 Mt 8.5 Mt 11.5 Mt 12.2 Mt 11.4 Mt 11.4 Mt 11.4 Mt

650 300 300 150 - - - -

5,661 4,941 - 2,572 2,881 2,572 2,584 2,584

1,311 6,424 8,246 8,785 9,327 8,784 8,784 8,784

6.9 Mt 9.8 Mt 11.4 Mt 10.9 Mt 11.6 Mt 12.2 Mt 12.3 Mt 12.4 Mt

2,442 3,585 3,672 3,693 3,704 4,348 4,348 4,348

1,474 1,750 2,217 2,346 2,698 2,668 2,704 2,805

3,030 4,491 5,507 4,869 5,233 5,233 5,233 5,233

- - - - - - - -

Internal Upmass Capability (FY)

(FY)

Baseline

CSOC

CRS

Margin (Shortfall)

Baseline Capability

CSOC Capability

CRS Capability

Internal Upmass Demand (FY)

Crew Supplies, Water, Gas

Maintenance / EVA Demand

Utilization Baseline

Contingency Maintenance7

USOS System Enhancements

Carbon Dioxide Removal Assembly (CDRA) “-4” Desiccant/Adsorbent Beds-

Monitoring

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

8


Continue replacement of legacy ISS avionics with Obsolescence Driven Avionics

Replacement (ODAR) components

Integrated Communications Unit (ICU) has been installed and activiated - doubling the downlink

data rate (300 Mbps) and an eight-fold increase in the uplink data rate (25 Mbps)

Increases crew communication loops with ground from 2 to 4.

Automatic switching between redundant Ku-band systems

6 channels of video down (was 4)

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

9


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

US Lab

COTS Wireless Access Points (WAP) placed inside the lab with external antennas to

provide the core wireless capability

Payloads/Users

Characterization of a wireless solution for the payloads/users to integrate and provide

piece parts to the developers

External Wireless users can connect using two methods:

Use an IEEE 802.11n Network Interface Card in their device

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.

Provide an IEEE 802.3 wired Ethernet interface and connect to Wireless Media Converter

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

10


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.

11

Four main focus areas

‒ Exploration technology demonstrations

» On-orbit demonstration or validation of technologies that enable or enhance exploration mission readiness

‒ Maturing critical systems

» Driving evolution in capabilities supporting the ISS today to meet future challenges - high reliability, high efficiency, low mass, low power

‒ Human health management for long duration space travel

» Research to understand the main risks to human health and performance

» Validation of strategies for keeping the crew healthy and productive

‒ Ops simulations and operations technique demonstrations

» Furthering our understanding of future operations challenges

» Gaining information which will enable efficient and effective mission design and operations approaches

Use of ISS to Prepare for Exploration

12

Current, Planned, or Proposed ISS

Technology Demonstrations, Nov 2012

Robotics Next Gen Canadarm testing (CSA)

Robotic Assisted EVA’s (Robonaut, NASA)

METERON (ESA) and Surface Telerobotics

Delay Tolerant Network Robotic Systems

Robotic Refueling Mission (CSA, NASA)

Robotic assembly to optical tolerances (OPTIIX, NASA)

Comm and Nav OPALS – Optical Communication

X-Ray Navigation, (NICER/SEXTANT, NASA)

Software Defined Radio (CoNNeCT/SCAN, NASA)

Delay tolerant space networks

Autonomous Rendezvous & Docking advancements (ESA/JAXA)

Advanced optical metrology (sensing/mat’ls)

Power Regenerative fuel cells

Advanced solar array designs [FAST, IBIS, or other]

Advanced photovoltaic materials

Battery and energy storage advancements [Li-Ion or other]

Thermal Control High efficiency radiators

Cryogenic propellant storage & transfer

Advanced materials testing

Closed Loop ECLSS Atmospheric monitoring: ANITA2 (ESA), MIDASS

(ESA), AQM (NASA)

Air Revitalization: Oxygen production, Next Gen OGA [Vapor Feed or other] (NASA)

Contaminated gas removal

Carbon Dioxide recovery: Amine swingbed and CDRA bed advancements

Advanced Closed-loop Life Support ACLS (ESA), MELiSSA (ESA),

Water/Waste: Electrochemical disinfection, Cascade Distillation System, Calcium Remediation, [Electrodialysis Metathesis or other]

Other Spacecraft Fire Safety Demonstration

Radiation protection/mitigation/monitoring

On-board parts repair and manufacturing

Inflatable Module (BEAM)

Italic = NRC High Priority Technology that would benefit from ISS access Underline = NRC High Priority Technology (focus for next 5 years)

13


Maturing Critical Systems • Radiation Environment Monitor - (NASA) demonstration of first generation of operational active personal

space radiation dosimeters • Amine Swingbed - (NASA) provide for environmental control of the habitable volume for human-rated

spacecraft by removing metabolically-produced carbon dioxide, and minimizing losses of ullage air and humidity

• Air Quality Monitor (AQM) – (NASA) volatile organic compound analyzer to be used to monitor the ISS environment

• Disruption Tolerant Networking for Space Operations (DTN) - (NASA) long-term, readily accessible communications test-bed, DTN is the comm standard for future spacecraft

• DOSIS-3D – (ESA) Determination of the radiation field parameters absorbed dose and dose equivalent inside the ISS with various active and passive radiation detector devices provided by ESA, JAXA and Russia. Aiming for a concise three dimensional dose distribution (3D) map of all the segments of the ISS.

• Exploration EVA Suit – (NASA) Could fly exploration suit as early as 2019. Will demonstrate and mature suit on ISS prior to use beyond LEO

• NASA Docking System - (NASA) Based on International specs agreed to by partners for exploration ISS will utilize and mature the system on ISS starting in 2015 with arrival of passive port.

14

Human Health and Performance Risks, Coordinated

Across All Partners

Mission

ISS

6 mo

Lunar

6 mo

NEA

(1yr)

Mars

(3yr)

Musculoskeletal: Long-Term health risk of Early Onset Osteoporosis

Mission risk of reduced muscle strength and aerobic capacity

Sensorimotor: mission Risk of sensory changes/dysfunctions

Ocular Syndrome: Mission and long-term health risk of Microgravity-Induced Visual Impairment

and/or elevated Intracranial Pressure (VIIP)

Nutrition: Mission risk of behavioral and nutritional health due to inability to provide appropriate

quantity, quality and variety of food

Autonomous Medical Care: Mission and long-term health risk due to inability to provide adequate

medical care throughout the mission (Includes onboard training, diagnosis, treatment, and

presence/absence of onboard physician)

Behavioral Health and Performance: Mission and long-term behavioral health risk.

Radiation: Long-term risk of carcinogenesis and degenerative tissue disease due to radiation

exposure – Largely addressed with ground-based research -

Toxicity: Mission risk of exposure to a toxic environment without adequate monitoring, warning

systems or understanding of potential toxicity (dust, chemicals, infectious agents)

Autonomous emergency response: Medical risks due to life support system failure and other

emergencies (fire, depressurization, toxic atmosphere, etc.), crew rescue scenarios

Hypogravity: Long-term risk associated with adaptation during IVA and EVA on the Moon, asteroids,

Mars (vestibular and performance dysfunctions) and postflight rehabilitation

Not mission

limiting

GO

Not mission

limiting, but

increased risk

GO

Mission

limiting

NO GO 15


SCAN

REBR

MISSE-8

Human Health Management for Long Duration Space Travel Weightlessness: greatest emphasis on understanding long-term physiological

effects of most unusual spaceflight factor, including newly identified risk affecting visual function • Hypogravity: 7 investigations from CSA, ESA, JAXA and NASA • Musculoskeletal: 6 investigations from ESA and NASA • Sensorimotor: 2 investigations from ESA and NASA • Ocular Syndrome: 1 investigation from NASA • Nutrition: 1 investigation from NASA

Internal and external environments: factors related to mechanics of spaceflight inside closed vehicle in dangerous natural environment • Toxicity: 2 investigations from NASA and ESA • Radiation: 1 investigation from CSA which supplements a major ground-

based research program Operational medical issues: development of medical solutions to problems

caused by physiological and environmental factors, with special attention to psychosocial effects of high autonomy at extreme distance from Earth

• Behavioral Health and Performance: 4 investigations from ESA and NASA • Autonomous Medical Care and Autonomous Emergency Response: 2

investigations from ESA


Ops Simulations and Operations Technique Demonstrations

Started

• Autonomous Procedure Execution – (NASA) Modification of several existing procedures to make more autonomously executable (add notes, troubleshooting steps, video, constraints, crew commanding)

• Crew User Interface System Enhancements (CRUISE) – (ESA) Voice activated procedure viewer

Future

• Instant Messaging (IM) Texting (countermeasure for voice communication delay) (NASA) (Summer 2013) • Crew Self Scheduling/Replanning on ISS (NASA and Roskosmos) (Summer 2013) • Communication delay testing - (NASA) Testing of voice communication delay implications to crew/ground

behavior and task execution (start date TBD) • Crew procedures interaction (NASA and ESA) - Using system telemetry embedded in procedures (start

date TBD) • Advanced Exploration Systems (AES)/Autonomous Mission Ops (AMO) – (NASA) Automating crew systems

management (start date TBD)

17

One-Year ISS Mission crewmembers

Scott Kelly

STS-103 in 1999, STS-118 in 2007,

ISS 25/26 in 2011

Mikhail Kornienko

ISS 23/24 in 2010.

18

Previous one-year fliers

Months 14 13 12 11 10

# 1 1 2 1 1

Year 1994-1995

1998-1999

1987-1988

1987-1988

1992

19

Categories of Biomedical Investigations

Risks currently not resolved

Evaluation of countermeasures

Physiological research on cost of

adaptation to spaceflight

Behavior and performance

Joint Biomedical Research Program for

Russian-US One-Year ISS Mission

20

Selection of Biomedical Investigations

Prioritization will consider (not in rank order)

Highest criticality for Mars Coordination with Russian investigations Heritage from previous flights Compatibility among candidate investigations for

co-manifesting on same crewmember(s) Efficiencies from data-sharing with other

investigations and medical requirements Resources — including mass, power, volume and

crewmember time (pre-, in-, post-flight) — for combinations of candidate investigations

Logistics required, especially for post-flight data collection

21

ISS Vision and Mission ISS Vision

A world renowned laboratory in space enabling discoveries

in science and technology that benefit life on Earth and

exploration of the universe

ISS Mission

To advance science and technology research, expand human knowledge, inspire and educate the next generation, foster the commercial development of space and demonstrate capabilities

to enable future exploration missions beyond low Earth orbit

22

Revised ISS Goals Goal 1: Maximize Science and Technology Research and development on the ISS to realize its full potential

Goal 2: Achieve Operational and Cost Efficiency with a high performance ISS team working in an optimal and inclusive Program structure

Goal 3: Raise Awareness of the ISS, its relevance and benefits in our daily lives and our future

Goal 4: Provide Global Leadership, strategic alliances and partnerships to fully utilize ISS capabilities to further research and exploration

Goal 5: Demonstrate capabilities that Benefit Space Exploration and Expand Our Reach Beyond Low Earth Orbit (LEO)

Goal 6: Use the ISS to Catalyze Commercial Development and Operations in Space

23

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