Rod Jones, Manager

NASA ISS Research Integration Office

AAS, June, 2014

ISS Orbit and Ground Track Applicability for Earth Observation,

Astrophysics and Heliophysics

ISS as a Platform for Earth Science

All geographic locations between 51.6 North and South latitude can

be observed NADIR pointing

Provides coverage of 85% of the Earth’s surface and 95% of the

world’s populated landmass every 1-3 days

ISS as a Platform for Earth Science

ISS coverage in 24 hrs for a 70°-swath optical payload. (Courtesy of ESA)

Processing lighting (changes with subsequent passes)

Promotes viewing over the same ground site at

different times of the day

ISS Characteristics Payloads are

Capitalizing On

• Earth observation repeatable every few days and

at different times of the day

• Cross comparison and corolation of data being

collected by instruments in ISS orbit to instruments

in other orbits

• Continuous measurements and analysis of the

Earth at a unique inclination and altitude

• The ability to change out sensors in flight

• The ability to deploy and retrieve samples in flight

On Orbit Payload Resources

Power 30kw average

Internal Payload Racks

13 NASA Lab

11 ESA Lab

10 JAXA Lab

External Sites

8 NASA Truss ELC Platform Sites

10 JAXA Platform Sites

4 ESA Platform Sites

Crew time Exceeding 35 hrs per week (average)

Facility to support visual and multispectral remote sensing using Lab Optical Window

Window Observation Research Facility (WORF)

US Laboratory Window

50-cm diameter

Telescope-quality optical glass

NADIR view

WORF Rack

Cupola

Bay window in space

80-cm diameter top

window

6 side windows

ISS External Platforms

Things to consider when selecting a

site and designing your payload

...ISS is a multi user platform

• Site field of views and obstruction’s • Platform stability and impacts to pointing • Torque Equilibrium Attitude changes from ISS growth • Attitude changes form visiting vehicles and EVA • Vibration from humans and systems • Flex of the structure • External Contamination Sources (launch vehicle & on-orbit) • Robotically compatible for installation and maintenance • Resource availability is not the same at all sites

Page No. 11

ISS_CM_019 (Rev 09/2011)

Pre-decisional, For Internal Use Only

Site Analysis

• Three ELC sites were assessed for TSIS:

– Solar Viewing

– FOV

– Contamination

– Clearance

– Data and Power Interfaces

ELC3 Site 3

Page No. 12

ISS_CM_019 (Rev 09/2011)

Pre-decisional, For Internal Use Only

Clearance Analysis TSIS at ELC 2-3 Location

Page No. 13

ISS_CM_019 (Rev 09/2011)

Pre-decisional, For Internal Use Only

Beta = 38 deg

ELC3-5 Obscured by Solar Panels at Sunrise

Page No. 14

ISS_CM_019 (Rev 09/2011)

Pre-decisional, For Internal Use Only

Page No. 15

ISS_CM_019 (Rev 09/2011)

Pre-decisional, For Internal Use Only

Viewing Time vs. Beta Angle

Page No. 16

ISS_CM_019 (Rev 09/2011)

Pre-decisional, For Internal Use Only

Viewing Time Per Orbit For 1 Year

ELC 3-5: Blockage by SCAN TB (~1 month)

ELC 2-3: Blockage by NICER (~1 month)

17

Momentum Manager Controller Peak to Peak Attitude Wobble Oscillation

For Stage configurations in the

foreseeable future, the predicted

TEA ranges are:

Roll: -1.0 ~ +3.0 deg

Pitch: -7.0 ~ +2.0 deg

Yaw: -15 ~ +15 deg.

Wobble oscillation

ISS as a Observation Platform Torque Equilibrium Attitude (TEA) and Wobble Oscillation Description

ISS External Vibratory Environment

for External Payload Pointing Instrument

ISS quiescent mode = No thruster firings, dockings, EVA, or robotics operations

Typical response, not worst case

Snapshot of 3 10-minute data takes

All data taken on March 16, 26, and 27, Stbd SARJ Rotating, exercise, 3 crew.

10-2

10-1

100

101

10-1

100

101

102

Freq

Mic

rog R

MS

SDMS S3 Max 1/3 Octave Band - GMT 076, 085, and 086

ULF-4 analysis concluded peak ELC rotations on the order of 0.03 degrees during quiescent mode

Data provided by Boeing, June 2010

Data measured on ISS S3 truss

ELC2 Payload Sites’ 2015 Contamination

Levels at -40°C

Boeing Space Environments Team

Angstroms/year

+X View -X View

Note: Legend scale is different from -10 and 25°C results.

Site 3

Site 7

Site 3 Site 7

• The International Space Station provides an exceptionally clean environment

to external payloads and science assets

• External contamination control requirements limit contaminant deposition to

130Å/year on external payloads and ISS sensitive surfaces

– Specified levels are lower than any previous space station (Mir, Skylab,

Salyut) by several orders of magnitude

• Measurements of contaminant deposition on ISS returned hardware have

demonstrated that requirements are met at ISS payload sites

Experiment Side Requirement (130Å/year)

Measured

MISSE 2 ram 520 Å (4 years) 50 Å

wake 520 Å (4 years) 500 Å

Node 1 nadir window cover

nadir 390 Å (3 years) 50 Å

ISS Contamination Environment Description

For Truss Attached Payload

Data provided by Boeing, June 2010

21

External Research Accommodations

Common Attachment System (CAS) Site

Mass capacity 1360 - 8618 kg

(3000 - 19000 lb)

Power 3 kW each on two lines

(primary, auxiliary)

Thermal Passive

Low-rate data 1 Mbps (MIL-STD-1553)

High-rate data 100 Mbps (shared)

Sites available to

NASA 6 sites

22

ExPRESS Logistics Carrier

Payload Resources

Mass capacity each site 227 kg (500 lb)

Volume 1 m3

Power

750 W, 113 – 126 VDC;

500 W at 28 VDC per

adapter

Thermal Active heating, passive

cooling

Low-rate data 1 Mbps (MIL-STD-1553)

Medium-rate data 6 Mbps (shared)

Sites available per ELC 2 sites

Total ELC sites

available

8 sites, building adapter

to add 2 more sites

External Research Accommodations

MISSE 7

Payload Sites

23

External Research Accommodations

Columbus External Resources

Mass capacity 230 kg (500 lb)

Volume 1 m3

Power 2.5 kW total to carrier

(shared)

Thermal Passive

Low-rate data 1 Mbps (MIL-STD-

1553)

Medium-rate data 2 Mbps (shared)

Sites available 4 sites

24

External Research Accommodations

JEM-EF Resources

Mass capacity

550 kg (1,150 lb) at

standard site

2,250 kg (5,550 lb) at

large site

Volume 1.5 m3

Power 3-6 kW, 113 – 126

VDC

Thermal 3-6 kW cooling

Low-rate data 1 Mbps (MIL-STD-

1553)

High-rate data 43 Mbps (shared)

Sites available 10 sites

46in (1168.4 mm)

31in (787.4mm)

PFRAM under surface

34in (863.6mm)

Unpressurized Cargo

Maximum Mass

Maximum Volume

Turnover Schedule

3310 Kg 14m3 L-30 days

Standard FRAM based Cargo Envelope

3-FRAM based Cargo in DRAGON Trunk

Unpressurized Cargo capabilities

SpaceX Trunk Specifications

Unpressurized Payloads

*Configuration shown based on standard

FRAM-based payloads that can launch

to Columbus and ELC payload sites.

SpaceX currently working on developing

“HCAM” interface for launching to JEM-EF

payload sites.

Robotics

JEM ARM

SSRMS

All External payloads are robotically compatible for installation and removal

Dexterous End Effector

SSRMS attachment which the ground team or on-orbit crew can

use robotically to install, remove and replace payloads and failed

components

Nano Racks Cube Sat Deployers

& Cube Sat’s Sponsoring Space Agency: NASA

Research Objectives NRCSD is a small satellite launching platform, providing

containment and deployment mechanisms for several individual

small satellites deployed from the International Space Station into

Earth orbit. CubeSat investigations with ascent on Orb-1 include:

• Dove, from Planet Labs, will form a constellation of Earth-

observing satellites.

• LituanicaSat-1 & LitSat-1, Lithuania’s first satellites, provide

real hands-on experience in satellite engineering.

• ArduSat-2 serves as a platform on which students and private

space enthusiasts may design and run their own space-based

experiments.

• UAPSat-1, Peru’s first satellite, will measure temperature and

weather, and contribute data on the behavior and capabilities of

satellites on orbit.

• SkyCube is a commercial imaging satellite.

LituanicaSat-1 LitSat-1 UAPSat-1 SkyCube Dove ArduSat-2

NRCSD launcher (installed on MPEP)

JEM Small Satellite Deployment

Capabilities in Development

Overall Platform: 52”L x 30”W x 3-9”H

Max Payload: 44”L x 30”W x 11-21”H; 100 kg

SSIKLOPS

JEM Airlock Slide Table

Robotic Arm Grapple Fixtures – Payload/SSIKLOPS maneuver,

Payload Deployment

Crew Interface – Payload Secure using IVA tool.

Payload Interface

Crew Interface – Pusher plate

pre-load Attachment Posts

w/guide pedals

Pusher Plate Mechanism

2 1 3 4

High Definition External Video

Technology Demonstration

ISERV Project Overview ISS SERVIR Environmental Research and Visualization System (ISERV) is an automated Earth-observing system in the Destiny module aboard the International Space Station (ISS). It is primarily a means to gain experience and expertise in automated data acquisition from the ISS that also provides valuable data for use in disaster monitoring and assessment, and environmental decision making.

Chris Hadfield Installing

ISERV in Destiny

ISERV Optical Characteristics

@ 420 km altitude Angular Spatial

Resolution 1.65 arcsec ~4 m

FOV 2.36o x 1.58 o ~17 km x ~11 km

Spectral 350nm to 800 nm

ISERV in WORF

Payload Volume

ISERV Launch

Configuration

ISERV Project Results

San Diego,

California

Mulanje,

Malawi

Nile River,

Sudan

Lake

Titicaca

Huntsville,

Alabama

Grand

Canyon

Andes Mts,

Chile

Floods in Calgary, AB, June 22, 2013 Floods/Landslides, N. India, June 28, 2013

SAGE III (2014)

OCO-3 (2017) CATS (2014) HICO (2009) RapidSCAT (2014)

ISERV (2012)

LIS (2016)

Snapshot of GEOS-4 model global aerosol

distribution forecast for March 20, 2006 Orange = dust; Blue = sea salt; Green = smoke and sulfate;

Saturation ~ species column amount

Cloud-Aerosol Transport System (CATS): Key Science Objectives

ISS orbit. The low-inclination orbit permits

extensive measurements over aerosol source

and aerosol transport regions.

• Demonstrate multi-wavelength aerosol and cloud retrievals. • Provide cloud and aerosol data to help bridge the gap between CALIPSO and

future missions. • Enable aerosol transport models with real-time data downlink from ISS • The ability of an aerosol plume to transport long distances is determined by its

injection height relative to the local planetary boundary layer (PBL). • Passive aerosol measurements from space provide valuable constraints on

column aerosol loading. However, models lack observational constraints on vertical distribution.

• ISS orbit is intriguing for tracking of plumes and study of diurnal effects (something not possible with A-Train orbit).

CATS Payload

• The CATS instrument is an attached payload for the Japanese Experiment

Module – Exposed Facility (JEM-EF) on the ISS.

• The lidar is based on existing aircraft instrument designs and uses photon-

counting detection with a high repetition rate laser.

• Launch is June 2014 on .

Hyperspectral Imager for the Coastal Ocean

(HICO) The HICO opportunity

Office of Naval Research sponsored HICO as an Innovative Naval Prototype (INP) demonstration Space Test Program provided the launch to the International Space Station Instrument mounted on JEM-EF

HICO program requirements

Launch and operate the first spaceborne coastal Maritime Hyperspectral Imager (MHSI) optimized for coastal environmental characterization Demonstrate scientific and naval utility of maritime hyperspectral imaging from space Serve as a pathfinder for future spaceborne hyperspectral imagers

HICO Current Status & Future Plans

HICO operations are funded by NASA ISS HICO data product generation and algorithm updates will be supported by NASA Earth Science

Approach:

• NPR 7120.8 and Risk Class E implementation

• Modify EM to operate at ISS orbit and attitude, including timing

changes • Build new hardware:

− P/L structure and thermal (radiators and MLI) for packaging on CEPA

− Dual pencil beam reflector and feeds − Power converter (120 VDC ISS power to 40 VDC P/L power) − Translator for RS-422 science telemetry to ISS Ethernet − Power and signal cables from P/L to CEPA

• Environmentally qualify integrated payload • Build new operations interfaces • One month on orbit checkout and 2 years operations

Rapid-SCAT on ISS

Radar scatterometer payload, mounted at an ISS nadir looking

external facility site, operates continuously for 24 months once

installed and checked out

• Payload: Utilize refurbished SeaWinds EM scatterometer hardware

with modification/augmentation to meet ISS payload

accommodation and operation requirements and certified for flight

and operations

− H-pol and V-pol pencil beams looking at about 45° from nadir,

scanning at about 18 rpm with 0.75 m (D) reflector

− 800-1000 km swath, covering within ±52° latitude in 48 hrs

− Wind resolution comparable to QuikSCAT

− Mass: 200 kg, Power: 250 W; Data Rate: 40 kbps, continuous

• GFE’d: CEPA/ExPA by JSC; TReK by MSFC

• Launch: SpaceX Dragon (but can be by JAXA HTV)

• Operations: Operated from JPL through the POIC at MSFC

• Data Processing: Processed by JPL, inheriting QuikSCAT

processor

• Data Distribution/Archive: NASA PO.DAAC

Implementation:

Description: Fly a radar scatterometer to

continue ocean vector winds (OVW)

measurements and to sample at all times of day

enabled by ISS orbits (in contrast to twice a day

sampling of sun-synchronous polar orbits) to

observe diurnal variability of ocean winds and

sea surface interaction not observable before

Objectives: • Continue more than 10-year Ku-band based

vector winds observations

• Investigate the global diurnal cycle and remove

the diurnal effect on scatterometer-based ocean

vector winds

• Improve cross-calibration of and provide

additional measurements to the international

OVW constellation

Nadir • Columbus External Facility

nadir site is the preferred location

• Alternate configuration for Express Logistics Carrier-1 nadir P/L site feasible but w/ more blockage

52°

Command &

Data

Subsystem

Electronics

Subsystem

CEPA

Baseplate

Reflector

Antenna on

Spin Assembly

Configurations:

QuikSCAT Sees Hurricane Katrina

Global Winds as

Viewed by QuikSCAT

Rapid-SCAT Configuration

Dual-Beam Reflector

and Feeds on Spin

Assembly

Command &

Data Subsystem

Scatterometer

Electronics

Subsystem

CEPA

Baseplate

50.5 in

(1282.7 mm)

At 90º Antenna Rotation

52.7 in

(1338.6 mm) 26.0

in

(660.4

mm

)

46.0 in

(1168.4 mm) At 180º Antenna Rotation

49.0

in

(1244.6

mm

)

ANTENNA SUBSYSTEM ELECTRONICS SUBSYSTEM

COMMAND & DATA SUBSYSTEM

OCO-3 Project Overview

Salient Features: Category 3 mission per NPR 7120.5E Risk classification C per NPR 8705.4 High-resolution, three-channel grating spectrometer (JPL) Partnership between SMD and HEOMD Deployed on the International Space Station Launch Readiness: 01 Oct 2016 on a Falcon 9 from KSC Operational life: 3 years

Primary Science Objectives • Collect the space-based measurements needed to quantify variations in the column

averaged atmospheric carbon dioxide (CO2) dry air mole fraction, XCO2, with the precision, resolution, and coverage needed to improve our understanding of surface CO2 sources and sinks (fluxes) on regional scales (≥1000 km).

Measurement precision and accuracy requirements same as OCO-2

Operation on ISS allows latitudinal coverage from 51 deg S to 51 deg N

OCO-3 is a NASA directed Climate Mission on the International Space Station

OCO-3 Requirements in Payload Interface Agreement

Mass 500 kg

Power 600 W

Data Rate 3 Mbps

Volume 1.85 m x 1.0 m x 0.8 m

Thermal Fluid Cooling Loop

Science and Application Objectives

• Lightning is quantitatively coupled to both thunderstorm and related

geophysical processes.

• Therefore lightning observations provide important gap-filling inputs

to pressing Earth system sciences issues in a wide range of

disciplines (e.g., weather, climate, atmospheric chemistry, lightning physics).

• Real time observations will be provided to operational users.

• LIS data is the “Gold Standard” for global lightning climatology.

Measurement

• LIS measures global lightning (amount, rate, radiant energy) during both day and night, with

storm scale resolution, millisecond timing, and high, uniform detection efficiency.

– LIS daytime detection is both unique and scientifically important (>70% occurs during day).

– Only LIS globally detects TOTAL (both cloud and ground) lightning with no land-ocean bias.

Mission Overview

• NASA developed and demonstrated space-based lightning observation as a remote sensing tool under Earth Observing System (EOS) and Tropical Rainfall Measuring Mission (TRMM) (LIS still operational on TRMM).

• LIS on the ISS will extend TRMM time series observations, expand latitudinal coverage, and provide real time observations in support of important and pressing science and applications objectives.

• Integrate as hosted payload on DoD Space Test Program (STP-H5) and launch on SpaceX Dragon in January 2016 for 2-4 year mission.

Lightning Imaging Sensor (LIS) on ISS

LIS Sensor Head and

Electronics Unit (20 kg, 30W, 128x128 CCD, 1 kB/s)

STP-H5 ( notional concept )

LIS Sensor

LIS Electronics

Science benefits gained by taking LIS to ISS

• Higher latitude lightning coverage

– Acquire the 30% lightning in N. Hemisphere summer missed by TRMM LIS leading to improved global lightning climatology

– Enhance regional and global weather, climate, and chemistry studies – Provide CONUS coverage (needed for National Climate Assessment)

• Real time lightning using ISS Low Rate Telemetry (LRT)

– Desired by SMD and strongly endorsed by NOAA partners (partners include: NWS Pacific Region, Joint Typhoon Warning Center, Ocean Prediction Center, Aviation Weather Center, and National Hurricane Center)

– Provide real time lightning for data sparse regions, especially oceans(storm warnings, nowcasts, oceanic aviation and international SIGMETs, long- range lightning system validation, hurricane rapid intensification evaluations)

• Simultaneous / complementary LIS observations on ISS – Provide critical daytime lightning to better understand mechanisms

leading to TGFs and TLEs (endorsed by ISS ASIM and GLIMS science teams)

• Cross-sensor calibration – Cross calibrate ISS LIS, TRMM LIS, GOES-R Geostationary Lightning Mapper

(GLM) and Meteosat Third Generation Lightning Imager for improved science and applications (strongly endorsed by NOAA and ESA)

TRMM LIS does NOT cover CONUS for climate and chemistry assessments

LIS detects lightning during the day when most lightning occurs

Real time LIS lightning useful for a host of operations (LIS in Hurricane Katrina)

SAGE III on ISS Project Description

Primary Science Objective:

Monitor the vertical distribution of aerosols, ozone and other

trace gases in Earth’s stratosphere and troposphere to

enhance understanding of ozone recovery and climate change

processes in the upper atmosphere

SAGE III on ISS directly supports NASA Strategic Goals to

extend and sustain human activities across the solar system;

expand scientific understanding of the Earth and the universe

in which we live

www-sage3oniss.larc.nasa.gov

www-sage3oniss.larc.nasa.gov

LaRC

JSC/ISSP

ESA

RiskNPR 7120.5D/NM7120.81 Category 3 / NPR 8705.4 Payload Risk

Class C

Launch August 2014 (Space X)

Orbit ISS Mid-Inclination orbit

Life 3 years (nominal) / ISS manifest through 2020 for extended mission

Payload

Sensor Assembly (LaRC), Hexapod (ESA), CMP (LaRC), ExPA

(JSC/ISS), ICE (LaRC), HEU (ESA), IAM (LaRC), DMP (LaRC) Nadir

Viewing Platform (LaRC)

540 W (CBE, mix between 120Vdc and 28 Vdc)

460 kg (CBE)

Mission Implementation

Partners

Mass &

Power

SAGE produces vertical profiles of aerosols and gases in the stratosphere and upper troposphere

The multi-decadal SAGE ozone and aerosol data sets have undergone intense scrutiny and are the international standard for accuracy and stability

SAGE data has been used to monitor the effectiveness of the Montreal Protocol (January 1989)

SAGE Science Results & Objectives