ISS Orbit and Ground Track Applicability for Earth Observation, Astrophysics and Heliophysics

Rod Jones, Manager NASA ISS Research Integration Office AAS, June, 2014 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

13 NASA Lab

Internal Payload Racks 11 ESA Lab

10 JAXA Lab

8 NASA Truss ELC Platform Sites

External Sites 10 JAXA Platform Sites

4 ESA Platform Sites

Crew time Exceeding 35 hrs per week (average) Window Observation Research Facility (WORF)

WORF Rack

US Laboratory Window 50-cm diameter Telescope-quality optical glass NADIR view

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

Site Analysis

• Three ELC sites were assessed for TSIS: – Solar Viewing – FOV – Contamination – Clearance – Data and Power Interfaces

ELC3 Site 3

Page No. 11 ISS_CM_019 (Rev 09/2011) Pre-decisional, For Internal Use Only

Clearance Analysis TSIS at ELC 2-3 Location

Page No. 12 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. 13 ISS_CM_019 (Rev 09/2011) Pre-decisional, For Internal Use Only

Page No. 14 ISS_CM_019 (Rev 09/2011) Pre-decisional, For Internal Use Only

Viewing Time vs. Beta Angle

Page No. 15 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) Page No. 16 ISS_CM_019 (Rev 09/2011) Pre-decisional, For Internal Use Only

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

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

Momentum Manager Controller Peak to Peak Attitude Wobble Oscillation

17 ISS External Vibratory Environment for External Payload Pointing Instrument

SDMS S3 Max 1/3 Octave Band - GMT 076, 085, and 086 2 Data measured on 10 ISS S3 truss

. ISS quiescent mode = No thruster firings, dockings, EVA, 1 or robotics operations 10

. Typical response, not worst case

. Snapshot of 3 10-minute data Microg RMS 0 takes 10

. All data taken on March 16, 26, and 27, Stbd SARJ Rotating, exercise, 3 crew. -1 10 -2 -1 0 1 10 10 10 10 Freq

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

Data provided by Boeing, June 2010 ELC2 Payload Sites’ 2015 Contamination Levels at -40°C +X View -X View Angstroms/year Site 7 Si Site 3 Si te te 3 7

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

Boeing Space Environments Team ISS Contamination Environment Description For Truss Attached Payload

• 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 Measured (130Å/year) MISSE 2 ram 520 Å (4 years) 50 Å wake 520 Å (4 years) 500 Å Node 1 nadir nadir 390 Å (3 years) 50 Å window cover

Data provided by Boeing, June 2010 External Research Accommodations

1360 - 8618 kg Mass capacity Common Attachment (3000 - 19000 lb)

System (CAS) Site 3 kW each on two lines Power (primary, auxiliary)

Thermal Passive

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

High-rate data 100 Mbps (shared)

Sites available to 6 sites NASA

21 External Research Accommodations

Mass capacity each site 227 kg (500 lb) ExPRESS Logistics Carrier Volume 1 m3 Payload Resources 750 W, 113 – 126 VDC; Power 500 W at 28 VDC per MISSE 7 adapter

Payload Sites Active heating, passive Thermal cooling

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

Medium-rate data 6 Mbps (shared)

Sites available per ELC 2 sites

Total ELC sites 8 sites, building adapter available to add 2 more sites 22 External Research Accommodations

Mass capacity 230 kg (500 lb)

Columbus External Volume 1 m3 Resources 2.5 kW total to carrier Power (shared)

Thermal Passive

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

Medium-rate data 2 Mbps (shared)

Sites available 4 sites

23 External Research Accommodations

550 kg (1,150 lb) at standard site Mass capacity 2,250 kg (5,550 lb) at JEM-EF Resources large site

Volume 1.5 m3

3-6 kW, 113 – 126 Power VDC

Thermal 3-6 kW cooling

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

High-rate data 43 Mbps (shared)

Sites available 10 sites 24 SpaceX Trunk Specifications Unpressurized Payloads

Unpressurize Maximum Maximum Turnover Schedule d Cargo Mass Volume 3310 Kg 14m3 L-30 days

Unpressurized Cargo capabilities

31in (787.4mm)

PFRAM under surface 3-FRAM based Cargo in DRAGON Trunk

*Configuration shown based on standard 34in (863.6mm) FRAM-based payloads that can launch to Columbus and ELC payload sites. 46in (1168.4 mm)

SpaceX currently working on developing “HCAM” interface for launching to JEM-EF Standard FRAM based Cargo Envelope payload sites. Robotics

JEM ARM

All External payloads are robotically compatible for installation and removal

SSRMS 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.

NRCSD launcher (installed on MPEP)

LituanicaSat-1 Dove UAPSat-1 ArduSat-2 SkyCube LitSat-1 JEM Small Satellite Deployment Capabilities in Development

SSIKLOPS

Payload Pusher Plate Interface Mechanism

1 2 3 4

JEM Airlock Slide Table Crew Interface – Crew Interface – Payload Secure Attachment Posts Pusher plate using IVA tool. Robotic Arm Grapple Fixtures – w/guide pedals pre-load Payload/SSIKLOPS maneuver, Payload Deployment . Overall Platform: 52”L x 30”W x 3-9”H . Max Payload: 44”L x 30”W x 11-21”H; 100 kg 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.

ISERV Launch Chris Hadfield Installing ISERV in WORF Configuration ISERV in Destiny Payload Volume @ 420 km altitude Angular Spatial ISERV Optical Resolution 1.65 arcsec ~4 m Characteristics FOV 2.36o x 1.58 o ~17 km x ~11 km Spectral 350nm to 800 nm ISERV Project Results

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

San Diego, Mulanje, Nile River, Lake Huntsville, Grand Andes Mts, California Malawi Sudan Titicaca Alabama Canyon Chile LIS (2016)

SAGE III (2014) ISERV (2012) OCO-3 (2017) CATS (2014) RapidSCAT (2014) HICO (2009) Cloud-Aerosol Transport System (CATS): Key Science Objectives • 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).

Snapshot of GEOS-4 model global aerosol ISS orbit. The low-inclination orbit permits distribution forecast for March 20, 2006 extensive measurements over aerosol source Orange = dust; Blue = sea salt; Green = smoke and sulfate; and aerosol transport regions. Saturation ~ species column amount 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 Rapid-SCAT on ISS

Description: Fly a radar scatterometer to continue ocean vector winds (OVW) Configurations: 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 CEPA vector winds observations Global Winds as Baseplate Viewed by QuikSCAT • Investigate the global diurnal cycle and remove the diurnal effect on scatterometer-based ocean vector winds 52° • Columbus External Facility • Improve cross-calibration of and provide Nadir additional measurements to the international nadir site is the preferred OVW constellation Electronics location Subsystem • Alternate configuration for QuikSCAT Sees Hurricane Katrina Reflector Express Logistics Carrier-1 Approach: Antenna on Command & Spin Assembly Data nadir P/L site feasible but w/ Radar scatterometer payload, mounted at an ISS nadir looking Subsystem external facility site, operates continuously for 24 months once more blockage installed and checked out Implementation: • Payload: Utilize refurbished SeaWinds EM scatterometer hardware with modification/augmentation to meet ISS payload • NPR 7120.8 and Risk Class E implementation accommodation and operation requirements and certified for flight • Modify EM to operate at ISS orbit and attitude, including timing and operations changes − H-pol and V-pol pencil beams looking at about 45° from nadir, • Build new hardware: scanning at about 18 rpm with 0.75 m (D) reflector − P/L structure and thermal (radiators and MLI) for packaging on − 800-1000 km swath, covering within ±52° latitude in 48 hrs CEPA − Dual pencil beam reflector and feeds − Wind resolution comparable to QuikSCAT − Power converter (120 VDC ISS power to 40 VDC P/L power) − Mass: 200 kg, Power: 250 W; Data Rate: 40 kbps, continuous − Translator for RS-422 science telemetry to ISS Ethernet • GFE’d: CEPA/ExPA by JSC; TReK by MSFC − Power and signal cables from P/L to CEPA • Launch: SpaceX Dragon (but can be by JAXA HTV) • Environmentally qualify integrated payload • Operations: Operated from JPL through the POIC at MSFC • Build new operations interfaces • Data Processing: Processed by JPL, inheriting QuikSCAT • One month on orbit checkout and 2 years operations processor • Data Distribution/Archive: NASA PO.DAAC Rapid-SCAT Configuration

Dual-Beam Reflector Command & and Feeds on Spin ANTENNA SUBSYSTEM ELECTRONICS SUBSYSTEM Data Subsystem Assembly

Scatterometer Electronics Subsystem

CEPA Baseplate

COMMAND & DATA SUBSYSTEM

50.5 in 52.7 in

(1282.7 mm) (1338.6 mm)

in

26.0 26.0

(660.4 mm) (660.4

mm)

49.0 in 49.0 (1244.6 (1244.6

46.0 in At 180º Antenna Rotation At 90º Antenna Rotation (1168.4 mm) OCO-3 Project Overview

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

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 Lightning Imaging Sensor (LIS) on ISS 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. LIS Sensor Head and Electronics Unit Measurement (20 kg, 30W, 128x128 CCD, 1 kB/s) • 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. Science and Application Objectives LIS Sensor • 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 LIS Electronics disciplines (e.g., weather, climate, atmospheric chemistry, lightning physics).

STP-H5 ( notional concept ) • Real time observations will be provided to operational users. • LIS data is the “Gold Standard” for global lightning climatology.

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) TRMM LIS does NOT cover CONUS for climate and chemistry assessments • 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 Real time LIS lightning useful for a host – Provide critical daytime lightning to better understand mechanisms of operations (LIS in Hurricane Katrina) 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)

LIS detects lightning during the day when most lightning occurs SAGE III on ISS Project Description www-sage3oniss.larc.nasa.gov 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 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 Mission Implementation LaRC Partners JSC/ISSP ESA NPR 7120.5D/NM7120.81 Category 3 / NPR 8705.4 Payload Risk Risk Class C Launch August 2014 (Space X) Orbit ISS Mid-Inclination orbit Life 3 years (nominal) / ISS manifest through 2020 for extended mission Sensor Assembly (LaRC), Hexapod (ESA), CMP (LaRC), ExPA Payload (JSC/ISS), ICE (LaRC), HEU (ESA), IAM (LaRC), DMP (LaRC) Nadir Viewing Platform (LaRC) Mass & 540 W (CBE, mix between 120Vdc and 28 Vdc) www-sage3oniss.larc.nasa.gov Power 460 kg (CBE) SAGE Science Results & Objectives . 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)