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

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