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["F1","F2","F3","F4","F5","H1","H2","H3","H4","J1","J2","J3","J4","Pri-order","Abbrev.","Mission","Type","Advocate","Objectives","Description","Measurement Strategy","Technologies","Risk","Class","Sequence","Status"]
[10,10,10,0,10,0,10,3,7,7,0,7,10,1,"MMS","Magnetospheric Miultiscale ","STP","Slavin","Understand the fundamental plasma physics processes of reconnection, particle acceleration, and turbulence from microscales to mesoscales. ","4 spin-stabilized spacecraft in a tetrahedron constellation (2 year mission)\nInter-spacecraft ranging system\n4 orbital phases:\nPhase 1:  1.2 RE by 12 RE, 10 incl. (9 months)\nPhase 2:  1.2 RE by 30 RE, 10 incl. (3 months)\nPhase 3:  8 RE by 100-120 RE lunar assist maneuver to achieve ~90 orbit plane change\nPhase 4: 10 RE by 40 RE, 90 incl. (11 months)\n","4 suites of identical instruments: electric field, energetic particles, hot plasma & magnetometer\nMeasurements taken during 4 phases include:\nPhase 1:  Dayside Magnetopause:  reconnection acceleration, turbulence, solar wind entry\nPhase 2:  Nightside Substorm:  reconnection, plasma sheet boundry, accel., current disruption\nPhase 3:  Magnetotail:  reconnection structures and dynamics, plasma escape/motion across boundary\nPhase 4:  Post-Cusp Magnetopause:  northward re- connection, reverse convection, pointing flux entry\n","None enabling. ",null,"MED/SM",null,"Phase A  Study Selection"]
[3,7,10,0,7,0,10,10,10,7,0,3,10,2,"ITSP","Ionosphere-Thermosphere Storm Probes","LWS","Forbes","• Identify and quantify the causes for mid-latitude ionospheric-thermospheric variations, including:\n  -the response to solar extreme ultraviolet radiation\n  -the response to geomagnetic storms\n  -sources and characteristics of ionospheric       irregularities\n","•Two spacecraft in 60° inclination circular orbits at nominal altitudes of 400 - 450 km and 10-15° azimuthal separations.\n•An ionosphere-thermosphere imager on a mission of opportunity (not necessarily concurrent with I-TSP) maximizes scientific return. ","•In situ measurements of parameters relevant to the plasma-neutral coupling, in particular neutral winds and composition.\n•Spacecraft inclinations provide good sampling of longitudinal variations at middle latitudes\n•Azimuthal separation provides good sampling of gradients.\nImager observations of neutral composition and ionosphere provide a large-scale view of I-T structural evolutions.\nAn integral part of LWS Program:\n  Solar Dynamics Observatory provides EUV data\n  Radiation Belt Storm Probes provide magnetospheric   input.\n•Correlative studies with other ground based and spacecraft assets\n","Low magnetic and electric field disturbances",null,"SM",null,"STD Report, AO soon"]
[10,10,0,5,10,10,0,3,8,10,10,10,0,3,"SP","Solar Probe","LWS","LaBonte","Determine the structure and dynamics of the magnetic fields at the sources of the solar wind\nDiscover the flow of energy that heats the solar corona and accelerates the solar wind\nDetermine what mechanisms accelerate, store, and transport energetic particles\nExplore dusty plasma phenomena and their influence on solar wind and energetic particle formation\nImportant for Exploration – Only mission to directly explore region where solar energetic particles are energized\n"," • Example Mission Design\n   - Solar polar orbit to within 4 Rs of Sun\n   -    Jupiter gravity assist\n   -    Two solar flybys spaced over solar cycle\n   -    First flyby’s solar source regions visible from Earth\n • Flight System Concept\n   - S/C protected by primary/secondary heat shield system\n          -    Powered by 3 Multi-Mission RTGs\n          -    Fully integrated science payload\n          -    25 kbps real-time downlink and large data storage\n","High resolution in-situ measurements: plasma, suprathermal, and energetic particle distributions and composition; waves and fields; neutrons/gamma rays; dust\nPolar imaging above 20Rs, surrounding white light during flyby\nSupporting remote sensing from near-Earth imagers\n\n ","Thermal Protection System for 3000 Sun Environment\nKa-Band Telecommunications\nMulti-Mission RTGs\n",null,"LG",null,"JPL/APL Reports; STDT initiated 3/04"]
[5,10,5,0,7,0,10,3,5,10,0,7,10,4,"RBSP","Radiation Belt Storm Probes (IT and RB)","LWS","Fennell","• Characterize and understand the variability of energetic radiation belt ions and electrons by identifying and evaluating:\n  -Source,\n  -Loss, and\n  -Transport mechanisms","•Two spacecraft in nearly identical, low-inclination (<18o, 12o goal), highly elliptical (500 km  5.5 RE) ‘chasing’ orbits distinguish spatial from temporal variations.\n\n","(Concurrent observations by RBSP, ITSP, with EUV measurements from SDO, and Global IT Imaging):\nMeasure temporal variations and radial profiles of energetic charged particles, electric and magnetic fields in response to varying solar wind conditions\n•Simultaneous two-point measurements discriminate between temporal and spatial phenomena, distinguish local acceleration from radial transport.\n•Evolving spacecraft orbits provide observations over a wide range of radial and azimuthal separations. \nAn integral part of the LWS program: simultaneous LWS I-T Storm Probe observations define the ionosphere-thermosphere response.\nCorrelative studies with other ground-based and  spacecraft assets\n\n\n"," • Thermal Protection System\n • Multi-Mission RTGs\n",null,"SM",null,"STD Report, AO soon"]
[0,0,10,3,10,0,3,5,10,10,0,7,10,5,"MD","Mars Dynamics","MS05","Forbes"," • Characterize the temperature, density and wind structures of   Mars’ upper atmosphere (UA), 25-200 km\n • Understand the sources of variability of Mars UA\n • Understand how wave-wave interactions, wave-mean flow   interactions, and wave dissipation contribute to the mean state   and variability of Mars’ and Earth’s UA\n • Define the aerobraking and aerocapture environments for Mars   exploration spacecraft\n • Provide the data required to constrain GCMs and to develop   atmospheric models that support the manned exploration effort\n"," • Example Mission Design\n   - Delta IV Launch Vehicle, Trajectory: Type 1 (C3=8.5 km2/s2)\n     * Propulsive MOI into highly elliptical orbit with a periapsis       between 110 and 250 km (apoapsis 57,000 - 6,000 km)\n     * Aerobrake into second OPS orbit (550 km circular)\n   - Total of 2 years in Mars orbit\n • Flight System Concept\n   - Solar-array powered, 3-axis S/C\n   - Payload: 123 kg, 175 W (avg), 11 kbps (avg data rate)\n"," • F-P Interferometer: temperature, winds, airglow emissions\n • Radiometer: temp, density, pressure, CO2 density and   emissions; constituents\n • SS Laser: Rayleigh temperatures in atmosphere\n • Neutral Mass Spectrometer:\n • Accelerometer: atmospheric density"," • Possible Planetary Protection change in categorization from Category III to Category IV would entail increased cost (component selection)\n • Aerobraking - detailed configuration analysis is required to optimize drag configuration relative to desired ballistic coefficient.  Slower aerobraking would impact operations cost.\n • Aerobraking - autonomous termination of aerobraking (pop-up maneuver).  Assumed to be validated on prior missions (e.g. MRO)\n • Instrument Cost - significant percentage of overall cost.  Instrument cost models estimate much higher payload cost than that provided by advocates.\n• Raleigh LIDAR – Baseline version used for this report provides marginal results in the second orbit (at 550 km circular).  Instead, either a lower science orbit is needed or the mirror should be increased from 0.5 to 1.0 m.  Also, see power charts about how increasing power/size can increase signal/noise ratio. There are a number of trades to consider here.",null,"MED"]
[5,10,10,0,10,0,7,10,5,7,0,3,5,null,"AMS","Auroral Multiscale ","MS05","Cattell","To understand the electrodynamic connection between Earth’s ionosphere and magnetosphere\nWhat structures accomplish the connection?\nWhat is the electrical impedance and how is it established?\nWhat is the role of ionospheric feedback?\nHow does magnetospheric dynamics affect the coupling?\n","Four spacecraft flying in formation through the mid-altitude M-I coupling region, supported by on-board auroral UV imaging\n600 X 7,000 km orbits\nSmall orbital maneuvers to achieve near tetrahedral configuration at desired point in orbit\n","Measure j: B & precision attitude (0.02 maximum error)\nMeasure : DC E-field, particle distribution, || B necessary\nDistinguish waves, static structures: 10 sec timing\nIdentify kinetic processes via established signatures\nUV Auroral imaging\nEstablish context: motions, forms, and conductivity structures\nFOV focused along magnetic foot-point\nDaytime and nighttime imaging needed","Low mass and power instrument technology deveopment",null,"MED/SM"]
[7,6,10,7,5,5,0,1,10,2,5,6,0,null,"BC","Bepi-Colombo","MOO","Murphy","Measure the composition, state and distribution of mass within Mercury’s interior.\nMap Mercury’s intrinsic magnetic field and determine the nature of its interaction with the solar wind.\nMeasure the composition, density, and dynamic variations in the charged particles that populate Mercury’s magnetosphere.\nImage the entire surface of mercury at a resolution <100 m and determine its composition.\nDetermine if water ice exists in deep craters in Mercury’s polar regions.\nMeasure the composition and density of Mercury’s tenuous exosphere.\n","2-3 ESA/ISAS spacecraft using SEP and gravity assist (Moon, Venus, Mercury) to orbit Mercury\n(MPO) Mercury Polar Orbiter (ESA) (3AS)\n(MMO) Magnetospheric Orbiter (ISAS) (Spinner)\n(MSE) Mercury Surface Element (ESA (if approved)\nOption 1:  2 spacecraft on 2 separate Soyuz-Fregat Launchers as much as 1 year apart\nOption 2:  3 spacecraft on 1-Ariane V\nLaunch 2009-1010\n","Planetary orbiter (MPO):\n3-axis stabilized\nVisible/near IR camera, photon spectrometers (IR, UV, X-ray, gamma-ray), neutron spectrometer, accelerometer, K-band transponder\nMagnetospheric orbiter (MMO):\nSpin-stabilized\nMagnetometer, ion spectrometer, ion/electron analyser, cold plasma detector, energetic particle detector\nSurface element (MSE):\nPhysical properties and geochemistry package, camera, seismometer\nMPO remote sensing","Solar Electric Propulsion will be demonstrated on ESA’s technology mission, SMART-1 (2003)\nHigh Temperature (HT) MLI, HT coatings\nHT, high intensity GaAs solar cells\nHT, 2-axis large amplitude antenna articulation mechanism\nHT X/Ka high gain antenna reflector and feeds\nMiniaturized integrated electronics for HT environments\nMercury Horizon Sensor, HT Sun Sensors\nLander",null,"SM/MOO",null,"ESA AO Issued 4/04"]
[10,10,null,null,10,{"$nulls":4},5,null,5,null,null,"DBC","Dayside Boundary Layer Constellation","STP","Fuselier","Measure highly asymmetric and dynamic bow shock and magnetopause structures which regulate the solar wind’s impact on the magnetosphere. \nEstablish the casual relationship(s) between these boundary phenomena and corresponding solar wind, foreshock, and magnetosheath drivers.\n","Orbits: 3 orbit planes near equator with 30 deg separation\nActive precession to keep apogee on earth sun line\n11 “skimmers”per plane with 11 to 12 Re apogee\n1”monitor” per plane with ~ 20 Re apogee \n“Skimmer” separations range from 1 to 5 Re near  apogees in phase with those of “monitors” \n","Minimum measurement compliment to\nIdentify boundary layer, magnetopause and shock crossings\nDetermine timing over ~Re separations: ∆t ~ 60 seconds between SC\nMeasure solar wind & IMF (monitors)\nVector magnetic field\n~0.5 nT accuracy, ~0.1 nT resolution\n0.1 sec resolution (required to despin)\nPlasma\nIons: density, flow, temperature.  ~5 sec resolution\nElectrons: 50 eV to 1 keV. ~5 sec resolution.\n","No “enabling” technology required\nLow level long duration thrust needed for orbit precession – small solar sail potential",null,"MED",null,"STDT Report Update 2004"]
[10,7,0,0,7,10,0,0,0,7,10,7,0,null,"DOPPLER ","Solar Atmospheric Doppler Mapper","MS05","Hassler","• Determine the most relevant observational signatures of flare, CME, and Solar Particle Event (SPE) eruption \n• Identify precursor signatures which can be used to forecast flare, CME, and SPE eruption \n• Identify what is needed to improve our ability to nowcast and forecast space weather and SPEs to ensure safe human exploration \n• Identify the physical mechanisms of mass flow and energy release in the solar atmosphere\n• Determine the interaction and connectivity of structures throughout the solar atmosphere"," • Example Mission Design\n   - Pegasus launch\n   - 98°, 600 km sun-synch orbit for continuous solar viewing\n • Flight System Concept\n   - 3-axis stabilized platform with 30 arc-second pointing capability\n   - Payload: 26 kg, 24 W, 1.5 Mbps\n   - 30 arcsec (control), 15 arcsec (knowledge)"," • UV/EUV Imaging Spectrograph for flow velocities and energy    release signatures \n • Filter Magnetograph for surface magnetic field measurements\n • Chromospheric/Coronal EUV Imagers for morphology and dynamics\n • Energetic Particles (SEP) measurements for event characterization\n • Coronagraph for detection of Halo CMEs","High cadence imaging spectrograph development ;Low mass/power instrumentation Advanced communication/DSN for future deployment to Sentinel or Mars orbit locations ",null,"SM"]
[3,10,10,0,10,0,10,10,10,10,0,3,10,null,"GEC","Geospace Electrodynamics Connections ","STP","Earle","•Understand the response of the Ionosphere-Thermosphere system to Magnetosphere forcing\n• Resolve the dynamic coupling of the Ionosphere- Thermosphere system to the Magnetosphere","•A constellation of four spacecraft flying in formation  (Pearls-On-A-String) each carrying identical sets of nine instruments.\n•185 X 2,000 km; 83 degree inclination parking orbit\n•Orbital maneuvers, at select times, to lower perigee to an altitude of ~ 130 km, lasting up to one week\n","•Measure in-situ all relevant plasma-neutral coupling parameters\n•Spacecraft cross important high latitude magnetosphere-ionosphere coupling regions\n•Unequal, variable spacecraft spacings to resolve different scales\n•Low dips to altitude where atmosphere begins to dominate the plasma dynamics.","Aerodynamic Structures & Materials\nLow Magnetic & Electric Field Emissions\nBody Mounted Solar Arrays (ESC) with Lightweight/Rigid Booms \nPrecise formation flying\n",null,"MED/SM",null,"SDT Report"]
[0,5,10,0,10,3,10,10,3,7,0,0,5,null,"GEMINI","Geospace Environment Magnetosphere-Ionosphere-Neutral Imagers","MS05","Germany","Determine dynamic coupling between ionosphere and magnetosphere\nDetermine how magnetospheric energy is dissipated in the Ionosphere-Thermosphere (I-T) system\nDetermine the important feedback mechanisms from the I-T system to the magnetosphere\nDetermine global magnetospheric dynamics\n","Mission Design\n2 High Altitude Spacecraft (HAS) in 8Re circular near-polar orbit\nGround-based radar network covers 30 to 90 deg north and south latitudes\n2 year life\nPayload \n3 FUV, 1 EUV, 1 ENA Imaging instruments per S/C, nadir pointing with yaw about nadir\n~10 ground radar installations with 2 antennas each ","Two high altitude spacecraft with global ENA and EUV imaging magnetosphere, and high resolution global spectroscopic FUV imaging of the I-T system\nGround radar measurements coordinated with space-based sensors Orbit above radiation belts reduces shielding requirements and improves image signal/noise. ","No unusual risks identified ",null,"MED"]
[3,10,10,0,5,0,10,10,3,7,0,3,10,null,"GSRI","Geospace System Response Imager","STP ","Fennell","Determine dynamic coupling between ionosphere and magnetosphere\nDetermine how magnetospheric energy is dissipated in the Ionosphere-Thermosphere (I-T) system\nDetermine the important feedback mechanisms from the I-T system to the magnetosphere\nDetermine global magnetospheric dynamics\nDetermine causes and consequences of magnetospheric storms and sub-storms\n","Mission Design\n2 Low Altitude Spacecraft (LAS) in 500-km sun-synchronous (97.4-degree inclination)\n2 High Altitude Spacecraft (HAS) in 8Re circular orbit also at 97.4-degree inclination\nGround-based radar network covers 30 to 90 deg north and south latitudes\n2 year life\nPayload \nLAS F-P Interferometer plus in-situ ions and Mag field instruments nadir and RAM oriented\nHAS 8 Imaging instruments nadir pointing with roll about nadir\n10 ground radar installations with 2 antennas each\n","Two high altitude spacecraft with global ENA and EUV imaging magnetosphere, and high high resolution global spectroscopic FUV and x-ray imaging of the I-T system – all data available real-time\nTwo low altitude spacecraft with Fabrey-Perot interferometers and in-situ field and particle measurements\nGround radar measurements coordinated with space-based sensors\n","No “enabling” technology required\nNew enhancing technology should reduce spacecraft cost by 10%\n",null,"MED"]
[{"$nulls":14},"HIGO","Heliosperic Imager and Galactic Observer","STP","Roelof"," • Establish the 3-D Structure of the Interaction Region Between the   Heliosphere and the Local Galactic Environment\n • Determine the Nucleosynthetic Status of a Present-Day Sample of the Galaxy\n  and Explore the Implications of this Knowledge for Big Bang Cosmology, \n  Galactic Evolution, Stellar Nucleosynthesis, and the Birthplace of the Sun\n • Characterize the Physical State of the Local Interstellar Cloud and the   Nature of its Interaction with the Heliosphere\n • Map the Location and Establish the Characteristics of the Extended Inner   Source of Neutrals in the Heliosphere, and Set Limits on the Dust Density   in the Heliosphere\n • Search for molecules and the building blocks of life liberated by sublimation \n  of small comets, asteroids and grains (detectable through measurement of \n  pickup particles)\n","• Example Mission Design\n   - Delta II 2925 Launch, 745 kg @ C3 = 26.4 km2/s2 (25.3 min)\n   - V-EGA  (2-) Trajectory\n     * 2.8 year cruise, 2 year orbital science operations\n     * 1 x 4 AU Equatorial Final Orbit \n • Flight System Concept\n   - Spin-Stabilized Platform\n   - Solar Array Design\n   - Payload: 71 kg, 62 W, 1 kbps\n   - 628 m/s V\n   - 900 arcsec (control), 360 arcsec (knowledge)"," • Image the Heliopause using Global Sky Maps of 83.4 O+\n •  Image the Termination Shock using Energetic Hydrogen Atoms and Radio\n  Detection (2-5 kHz)\n • Determine the isotopic and elemental composition of the neutral portion   of the interstellar gas from measurements of pickup ions and of the main    neutral species\n • Determine the Flow Direction, Speed and Temperature of Interstellar Atoms\n • Determine Composition and Radial Profiles of Extended Inner Source    Pickup Ions\n • Determine Time-dependent Interactions of Large-Scale Structures with    Heliospheric Interfaces through Radio Detection (2-5 kHz)"," • High resolution diffuse EUV Spectrometer\n • Advancing anti-coincidence noise\n  suppression technique\n • Negative Ion Conversion Surface",null,"MED",null,"Report 7/04"]
[{"$nulls":14},"HS","HelioStorm","MS05","Gopalswamy"," • Determine the structure of the solar wind on spatial and temporal   scales that are relevant for driving magnetospheric processes\n • Provide warning time for ground based infrastructure\n • Provide warning time to protect lunar and Earth-orbiting assets\n • Provide a pathfinder for the L1-Diamond science mission\n • Provide a demonstration platform for Exploration\n"," • Example Mission Design\n   - Delta IV Launch Vehicle\n   - Trajectory: ballistic transfer from Earth to L1 Halo (~90 days),     solar sail transition from L1 to 0.98 AU OPS station\n   - Continuous Solar Viewing: 2 years In Final Orbit\n • Flight System Concept\n   - Solar-array powered S/C with solar sail\n   - Payload: Fields and Particles+ Imaging (33 kg/24 W)\n"," • Energetic particles provides warning of strength and distance   of approaching interplanetary shock\n • Radio: With other spacecraft, one can triangulate the location   of interplanetary shocks\n • Energetic particles provide environmental data for lunar   missions (although very little warning) \n • Plasma/Magnetic Field provide warning and environmental   data for lunar missions and for Earth\n • Optical system provides diagnostics during sail deployment   and check-out"," • Solar Sail Demonstration/Validation Reqd.\n   - ISP Solar Sail Development Funding\n   - NMP Candidate Tech for Phase A Study\n • Solar Sail Navigation Tools\n   - ISP Development Funding\n • Autonomous Thrust Vector Control\n • “Multi-Chip Module” (MCM) Electronics\n   - micro-packaged MCMs on 2-6U cPCI cards by 2014",null,"SM"]
[{"$nulls":14},"IE","Io Electrodynamics","OTHER","Cattell"," • Investigate the Energy Conversion Processes in a  Magnetized   Plasma\n • Understand Mass Transport in a Rapidly Rotating   Magnetosphere\n • Determine How Intense Parallel Electric Fields are Generated   in a Magnetized Plasma\n • Determine How Momentum is Transferred Through Field-   Aligned Current Systems\n • Determine the Role of Io on Radio Wave Generation at Jupiter\n"," • Example Mission Design\n   - Delta III Launch: Direct Trajectory\n   - Elliptical Io-Resonant Equatorial Orbit\n     * 5.9 Rj x 71 Rj , ~ 1 mo. Orbital Period\n     * 2-Year Flight Time, 3-Year OPS\n • Flight System Concept\n   - Rad-Hard Spin-Stabilized Platform\n   - Chem/Bi-Prop w/ ARPS Implementation\n   - Payload:\n     * Fields & Particles Instrumentation (Plasma, Energetic       Particle, Magnetic & Electric Fields)\n     * UV Imager\n"," • Multiple Flybys of Io\n • Different Science Emphasis for Each  Encounter/Flyby\n • High Resolution Flyby Data Stored in Mass Memory for   Playback Over Post-Encounter Trajectory (Apojove)\n • Image Jupiter aurora to track magnetic footprint of Io"," • Rad-Hard Electronics/ ACS Sensors\n • Advanced Radioisotope Power",null,"LG"]
[0,10,0,0,3,10,0,5,0,10,5,10,0,null,"IHS","Inner Heliosphere Sentinels","LWS","Liewer"," • Determine how the global character of the inner heliosphere   changes with time\n • Understand how geo-effective structures (CMEs, shocks,   CIRs) propagate and evolve from Sun to 1 AU\n • Discover what solar dynamic processes are responsible for   the release of energetic particles and geo-effective events\n • Constrain heliospheric models\n"," • Example Mission Design\n   - Delta II or III Launch Vehicle\n   - Trajectory:Ballistic w/ Venus Gravity Assist(s)\n   - Elliptical Heliocentric Orbits\n     * Rp = 0.4, 0.45, 0.72, 0.72 AU      * Ra = 0.76, 0.79, 0.8, 0.95 AU\n   - 0.5 – 1 yr cruise, 4.5 – 4 yr  science ops\n • Flight System Concept\n   - Spin Stabilized (4 Dual-String S/C)\n   - Solar Array Implementation\n   - Telecom: X-band UP, Ka-band DOWN\n"," • Magnetic field, solar wind particle distribution, energetic    particle and radio and plasma wave measurements\n •  Longitudinally distributed and concentrated observations"," • High Temperature Solar Arrays\n • Advanced Thermal Control\n • Low Mass/Power High-Density Data Storage",null,"MED/SM",null,"SDT Initiated 2004"]
[3,10,10,0,5,0,10,10,3,7,0,3,10,null,"IMC","Inner Magnetospheric Constellation","LWS","Moore","Create time-dependent maps of the inner magnetosphere (1.5-12 RE)\nFully specify and understand the space environment where spacecraft and astronauts work.\nDiscover the origin and dynamics of magnetospheric particle populations\nDerive the global, time-dependent magnetic and electric fields.\nDetermine the development and evolution of magnetic storms.\n","2 “petal” low inclination orbits that maintain uniform coverage independent of precession.\n3 satellites per orbit, 6 total. \nInstruments: 3-axis Magnetometer, Electron Analyzer, Energetic Particles, 2-axis Electric Fields\n","The large-scale equatorial electric & magnetic fields are directly measured.\nAn independent measurement of the fields - integrated along particle drift paths - is obtained from the energetic particle phase space density contours.\nDifferent energies have different drift paths and highly constrain the construction of global synoptic “weather maps” of the inner magnetospheric response to geomagnetic disturbances originating on the Sun..\nDirect measurement of the origin and dynamics of global particle structures such as the ring current, the relativistic electron radiation belts, the plasmasphere and detached/extruded plasmaspheric populations.\n","No “enabling” technology required\nNew enhancing technology should reduce spacecraft cost by 10%\n",null,"MED",null,"Report 6/03"]
[{"$nulls":14},"IsP","Interstellar Probe (2)","VM","Roelof"," • Explore the interstellar medium and determine directly the   properties of the interstellar gas, the interstellar magnetic field,   low-energy cosmic rays, and interstellar dust\n • Determine the structure and dynamics of the heliosphere, as an   example of the interaction of a star with its environment\n • Study, in situ, the structure of the solar wind termination shock,   and the acceleration of pickup ions and other species \n • Investigate the origin and distribution of solar-system matter   beyond the orbit of Neptune \n"," • Example Mission Design*\n   - Delta II 7425 Launch (719 kg Cap., C3 = 0 km2/s2)\n   - Flight System Launch Mass: 564 kg\n   - Solar Sail Trajectory Targeted for Nose of Heliosphere\n     * 0.25 AU Solar Pass, 200 AU in 15 yrs. \n • Flight System Concept\n   - “Flying Antenna” Design Implementation (191 kg)\n   - Sized for 30 year Operations\n   - Payload: Fields & Particles + Imaging\n"," • Measure, in situ, the properties and composition of interstellar   plasma and neutrals, low energy cosmic rays, and interstellar dust\n • Determine the structure and dynamics of the heliosphere with in   situ measurements and global imaging\n • Map the infrared emission of the zodiacal dust cloud, measure in   situ the distribution of interplanetary dust, and determine the   radial distribution of small Kuiper Belt objects"," • Solar Sail: < 1 g/m2, 200 m radius\n • DSN 70m Subnet w/ Ka-band Uplink\n • Next Generation ARPS\n • Next Generation System On A Chip\n • Ka-band S/C Components and Phased Array\n • Hot-Gas Propulsion\n • Micro-S/C Technology\n • Low Mass/Power Instrumentation",null,"LG",null,"VM (2): 2001-2 Reports"]
[0,5,10,0,10,3,10,10,3,7,0,0,7,null,"ITMC","Tropical Ionosphere Thermosphere Mesosphere Coupler","STP","Germany","Understand how large-scale neutral winds, gravity  waves, and ion drifts are coupled in the low latitude upper atmosphere and how they respond to solar variations and to variable influences from the lower and middle atmosphere.\nDiscover the cause of planetary-scale plasma upwellings at low latitudes and investigate the effect of unstable flux tubes on inner plasmasphere dynamics.\nExplain the chaotic and explosive transfer of energy between irregularity scale lengths ranging from 1000 km to 1 cm which occur in the low latitude ionosphere at night.\nDetermine the extent and significance that tropical storms in the troposphere play in producing localized electric fields and neutral gas motions in the ionosphere.\n","3 satellites with identical orbit periods and the same low inclination (<20°)\n2 with elliptical orbits (250 x 1500 km)\nApogees:  180 degrees apart\nDipping to low perigee \n1 with a circular orbit of 600 km\nPayload (ram and nadir pointing)\n8 in-situ instruments on all 3\n4 remote sensing on circular spacecraft\n","A suite of 10 instruments for in-situ measurements on each of two dipping spacecraft and a suite of 11 in-situ and remote sensing instruments on one circular orbiting spacecraft.\nReplication of instruments and spacecraft to the fullest extent possible to minimize non-recurring engineering costs.\nBuild upon experience gained from the Global Electrodynamics Constellation mission.\nRemote sensing:  gravity waves, airglow, neutral winds, plasma density profiles;\nIn-situ:  electric, magnetic fields, thermal, energetic plasma, neutral properties, winds, lightning; \nCoverage (continuous in each orbit):\nConjunctions of the two elliptical satellites with each other and the circular satellite provide investigations of vertical coupling\n","Spacecraft with low perigee dipping capability, reductions in instrument size, mass, and power.",null,"MED"]
[0,0,10,0,10,0,5,10,10,10,0,0,3,null,"ITMW","Ionosphere Thermosphere Mesophere Waves Coupler","MS05","Earle","Global measurements of small scale gravity waves in the MLTI region\nDetermine the echange rate of water vapro between the troposphere and thermosphere","2 satellites in 650 km circular orbits\n30°: 2 years lifetime beginning when both satellites are on orbit\n70°: 6 years lifetime for water vapor measurement (desired)\nPayload (nadir and ram pointing) \n5 remote sensing\n2 in situ instruments\n","Type\nOptical remote sensing of airglow emissions, cloud height, wind fields, and water vapor\nIn situ measurement of electron and ion densities\nCoverage\nAll latitudes and local times\nWeekly sampling periods\n","Low Risk:  All instruments are at a Technology Readiness 7 or greater",null,"SM"]
[5,10,5,0,10,3,3,0,5,10,0,5,10,null,"JPO","Jupiter Polar Orbiter","OTHER","Liemohn"," • The Relative Contributions of Planetary Rotation and of the    Interaction with the Interplanetary Medium to Jovian   Magnetospheric Dynamics\n • How Global Electric and Magnetic Fields Regulate the Processes   that Produce the Radiation Belts, Plasma Sheet, and the Aurora\n • Identify the Particles Responsible for the Generation of the Jovian   Aurora and Determine their Magnetospheric Source Regions\n"," • Example Mission Design\n   - Delta III/Star 48 Launch , 1658 kg @ C3 = 31 km2/s2 (28.1 min)\n   - Elliptical Polar Orbit\n     * 1.1 Rj x 40 Rj, 75° inclination\n     * 4.6 Year cruise, 1-Year OPS\n • Flight System Concept\n   - Rad-Hard Spin-Stabilized Platform\n   - Solar Array Implementation\n   - Payload: Field & Particles, Imagery, Radio Science\n     * 55 kg, 38 W, 4 kbps\n   - 1758 m/s V\n   - Capability Driven Design\n     * 900 arcsec (control), 36 arcsec (knowledge)\n"," • Measure Particles and Fields In-Situ in the Auroral Acceleration   Region, Along L Shells, and in Conjugate Magnetospheric Source   Regions\n • Radio occultations of ionosphere and upper atmosphere\n • Image Aurora in the Visible and UV\n • Measure the Magnitude and Configuration of the Near-Planet    Magnetic Field and Map the 3-D Structure of the Radiation Belts"," • Radiation Hard Components\n • Adaptive Feed/Uplink Beacon\n • Internal 2-axis Slow Scanning Mirror IMC\n • TDI Image Synthesis and Relative Motion Cancellation \n • Synchronized Shutter for Imager Radiation Shielding \n • Ka-band Transponder/TWTA/Switches",null,"MED",null,"New Frontiers Step 2- JUNO"]
[{"$nulls":14},"L1D","L1-Diamond","LWS","Pizzo"," • Measure the properties of solar-wind turbulence (as seen in density,   velocity vector and magnetic field) as a function of separation in   space and time, ranging from the dissipation scales of perhaps   hundreds of kilometers to the outer scale of millions-of-kilometers\n • Direct measurements of the possible spatial symmetries of the   turbulence\n • Discover associations of the turbulence with suprathermal and   energetic particles\n • Measure the spatial variation in convected and propagating waves,   shocks and other disturbances in the solar wind\n"," • Example Mission Design\n   - Delta Launch Vehicle\n   - Trajectory: ballistic transfer from Earth to L1 (~90 days), solar     sail transition from L1 to constellation stations,\n     * 3 s/c in triangle formation, centroid 280 - 500 Re sunward       of Earth on Sun-Earth line, 4th s/c above the ecliptic\n     * Variable constellation baseline (for 3-D structure)\n   - Continuous Solar Viewing: 3 years In Final Orbit\n • Flight System Concept\n   - 4 solar array powered S/C with solar sails\n   - Payload: Fields and Particles (~ 20 kg/25W)\n"," • 4-s/c constellation with varying separations to study the full range   of turbulence structures in both space and time\n •  High time resolution with time delays providing valuable correlations   between the observed quantities"," • Solar Sail\n • Solar Sail Navigation Tools\n • Autonomous Thrust Vector Control",null,"MED",null,"Report 10/04"]
[{"$nulls":5},10,null,10,null,10,null,10,null,null,"L1Star","L-one Star","OTHER","Pizzo"," • Measure solar wind plasma and magnetic field conditions and determine the mechanism by which small-scale fluctuations dissipate in plasmas.\n * Provide broadband observations that can serve as a global index of the Earth's climate.\n • Determine the daily cycles in total ozone, aerosols, and column water vapor at high temporal and spatial resolution\n"," • Mission Design\n  -  Launch on the space shuttle, early 2002. 3 months to travel 1.5 million kilometers from Earth to reach the vicinity of the L-1 orbit position, and another 3 months to enter its Lissajous orbit\n  - Coordinated observations of the Sun/solar wind and of the Earth\n","This 3-axis stabilized spacecraft is equipped with solar arrays, a reaction-wheel-based Guidance, Navigation, & Control (GN&C)System, and a hydrazine thruster system for orbit maintenance. The Observatory will use a Spacecraft Bus based on the SMEX-LITE system.\n  - Spacecraft Bus SMEX-Lite Bus modified for Shuttle launch & L1 environment\n  - Guidance, Navigation, & Control (GN&C): 4 wheels, gyro, Star tracker, sun sensorsSolar Arrays \n  - Modular Solar Arrays based on SMEX design\n  - Propulsion: Hydrazine\n  - Antenna: 1 High Gain2 Omni Antennas\n  - Communication: 100 to 200 kbps downlink / 2 kbps uplink","N/A",null,"SM",null,"Mission based on Triana s/c"]
[7,7,10,5,10,3,3,3,10,10,0,10,10,null,"MAP","Mars Aeronomy Probe","MS05","Slavin"," • Determine the altitude and solar zenith angle variation in the   composition, density and temperature of the neutral and ionized   components of the upper atmosphere\n • Determine the intrinsic magnetic field at Mars and how the solar   wind interacts with the upper atmosphere and ionosphere\n • Determine the major features of the circulation of the   atmosphere at all levels, in particular the middle and upper   regions\n • Investigate the oxidation of CO and organics and the   corresponding dearth of free oxygen and ozone\n"," • Example Mission Design\n   - Delta IV Launch Vehicle, Trajectory: Type 1 (TBD)\n     * Propulsive MOI into 150 km x 6000-10000 km (1 yr)\n     * Inclination change into “frozen” OPS orbit #2 (1 yr)\n   - Total of 2 years in Mars orbit\n • Flight System Concept\n   - Solar-array powered, 3-axis S/C\n   - Payload: 34 kg, 41 W (avg), >32 kbps (avg data rate)\n"," • Neutral Species Escape Rates, Isotopic Ratios, Densities,   Temperatures, Winds and Composition\n • Thermal Plasmas (Ions and Electrons), Pick-up Ions, Energetic   Particles and Magnetic and Electric Fields\n • Integrated Theory and Data Analysis Program\n • UV spectra for remote sensing of escaping atoms"," • Possible Planetary Protection change in categorization from Category III to Category IV would entail increased cost (component selection)\n • Aerobraking - detailed configuration analysis is required to optimize drag configuration relative to desired ballistic coefficient.  Slower aerobraking would impact operations cost.\n • Aerobraking - autonomous termination of aerobraking (pop-up maneuver).  Assumed to be validated on prior missions (e.g. MRO)\n • Mars Limb Sensor - Based upon current payload stability requirements, the development of a limb sensor would reduce the pointing complexity and cost of the ACS subsystem.",null,"MED/SM",null,"variants studied at JPL"]
[10,10,10,0,10,0,10,3,3,10,0,7,10,null,"MC","Magnetsospheric Constellation ","STP","Moore","• Determine how the magnetospherestores, processes, and releases energy from the solar wind interaction:\nHow does the magnetotail behave?\nHow are particles injected to form the radiation belts?\nHow does the magnetopause respond to thesolar wind? ","• Constellation of 30-36 ST-5 class s/c  \n•15 deg inclination, nested orbits  \n•Apogees from 7-27 RE, ΔV = 814 m/s  \n•Per s/c: 20 kg, 15 W, 1 kbps, 1deg pointing","Synoptic vector measurements of magnetic field, plasma flow, and energetic particles","None enabling. \nST5 design experience base.\nFab, assy., and testing techniques from Iridium, GPS, other commercial, DoD constellations. ",null,"MED/SM",null,"SDT Report Update 2004"]
[3,10,10,0,5,0,10,10,3,5,0,3,5,null,"MIO","Magnetosphere-Ionosphere Observatory","STP ","Fuselier","Determine what causes the aurora\nDetermine how 10's-100's of gigawatts of energy are extracted from the magnetotail\nProbe magnetosphere-ionosphere coupling\n","Main s/c contains a high-power electron gun\n3 satellite s/c in close cluster with main s/c \nGeosynchronous satellites remain magnetically connected full-time to ionospheric observatory\nAll s/c carry critical measurement instruments\nObservatory locates the beamspot within the auroral ionosphere\n","Find the magnetospheric end of auroral arcs\nVerify position from electron-beam connection \nMeasure plasma, flow, and field gradients in aurora using multiple s/c\nDiscriminate among auroral arc theories","Exploits technologies developed by NASA’s program in active space experiments. \nNew enhancing technology should reduce spacecraft cost by 10%\n",null,"MED"]
[{"$nulls":14},"MTRAP","Magnetic TRAnsition Region Probe","LWS","Bogdan"," • Discover, measure, and understand the 3D structure and dynamics\n  of the magnetic transition region between the photosphere and\n  upper chromosphere.\n •  Connect the structure and events in the magnetic transition region\n  with their photospheric roots and the magnetic stressing and\n  heating of the chromosphere and corona.\n • Resolve and measure the appearance, transport, and destruction of  magnetic field on the fundamental intergranular scales in the\n  photosphere. \n"," • Example Mission Design\n   - Delta IV Launch Vehicle (due to shroud requirement)\n   - Geo-synchronous, Earth-orbiting satellite \n     * 3 years In Orbit\n • Flight System Concept\n   - 3-Axis Stabilized Solar Inertial Observatory Platform\n   - Solar Arrays\n   - 751 Mbps link to Ground Terminal\n   - Payload: 570 kg, 330 W (peak), 750 Mbps\n   - 36-as control (payload implements 10-as with 1-as knowledge)\n"," • Visible/infrared maps/images of vector magnetic field, intensity, and\n  velocity in the magnetic transition region and the photosphere, with\n  large FOV (> 100,000 km), high resolution (< 100 km), and high\n  sensitivity (< 30 G, transverse).\n •   UV maps/images of line-of-sight magnetic field, intensity, and\n  velocity in upper chromosphere/lower transition region.\n •  EUV images and spectra of coronal structures in and around the\n  FOV of the magnetic transition region observations and with\n  comparable resolution. "," • Large, light weight, reflecting optics for use in visible near IR and vacuum ultraviolet\n • Extendable optical bench\n  • Large format (up to 16K x 16K pixels), low power, high QE at 150 nm, multiport CCDs. \n    • Image motion compensation/stabilization for large apertures and EUV\n • Variable Emissivity Surfaces\n • High Data Volume Ground Processing\n • Instrument Auto-Boresighting System\n • High Stability Platform\n • Compact PCI Cards\n • Ka-band Transponder/TWTA/Switches",null,"MED",null,"Report Due 10/04"]
[{"$nulls":14},"NO","Neptune Orbiter","VM","Russell","Map Neptune’s highly asymmetric magnetic field\nDetermine the magnetospheric structure as the highly oblique and offset magnetic field rotates with the planet\nDetermine the densities, compositions, and temperatures of magnetospheric plasma populations, and their distributions throughout the magnetosphere\nMeasure the plasma flows associated with the dynamics of the magnetosphere driven by the planet’s rotation and by the solar wind\nDetermine whether Triton has an intrinsic magnetic field, and characterize the plasma interaction with Triton and its atmosphere\nCompare the magnetosphere of Neptune with other planetary magnetospheres and compare the Triton-magnetosphere Interaction with the Galilean satellites of Jupiter and with the role of Titan in Saturn’s magnetosphere\n","Example Mission Design\nDelta/Altas Launch (Jupiter Gravity Assist Trajectory)\n9-12 yrs to Neptune + 2 yrs in orbit\nAerocapture, Optical Com, -S/C Technology\nAutonomous operation and navigation\nMultiple flybys of Triton\nFlight System Concept\nFields & Particles Instrumentation (Plasma, Energetic Particle, Magnetic & Electric Fields)\n","Thermal plasmas, energetic particles, magnetic and electric fields, plasma waves, and auroral measurements (including UV spectral imaging of Neptune and Triton)\nIntegrated theory and data analysis program involving numerical simulations processes, and energetic-particle acceleration under a variety of planetary magnetic-dipole orientations\n","Aerocapture (0.3 to 0.4 mass ratio)\nAdvanced Telecom:  Optical or large-diameter inflatable antenna\nAdvanced Radioisotope Power\nAutonomous spacecraft operations",null,"LG",null,"VM: Planetary with magnetospheric component"]
[10,10,{"$nulls":3},10,{"$nulls":4},10,10,null,null,"PASO","Particle Acceleration Solar Orbiter","STP ","Strachan","See IHS (Sentinels)\n • Understand particle acceleration mechanisms\n • Distinguish between flare and shock accelerated particles\n • Study location and nature of energy release and particle   acceleration.\n • Determine conditions for shock acceleration and evidence   for post-eruption magnetic reconnection.\n • Study active region evolution\n"," • Example Mission Design\n   - Delta II Launch (C3 = 0 km2/s2)\n   - Solar Sail Trajectory\n     * Transfer From 1 AU to a 0.169 AU Circular       Solar Equatorial Orbit (Period: 25.4 days) \n     * 3-Year Transition to Final Orbit\n   - Continuous Viewing of Active/CME Source Region\n     * 4-5 years In Final Orbit\n • Flight System Concept\n   - Spin-Stabilized Platform (500 kg [inc. 80 kg of Sci.])\n   - Advanced Thermal Design for 0.16 AU Orbit\n"," • High energy solar flare imager (< 1 arcsec)\n • 1-100 Mev/nuc, resolve composition up to Fe\n • Neutron spectrometer, > 5MeV neutrons\n • Gamma-ray spectrometer for nuclear lines\n •  Solar Wind and magnetic field instruments"," • Solar Sail @ 9 g/m2, 87 m Radius\n • High Temperature Solar Arrays\n • Solar Sail Navigation Tools\n • Autonomous Thrust Vector Control\n • Advanced Thermal Control",null,"MED"]
[10,10,0,0,7,7,0,5,8,0,10,0,0,null,"RAM","Reconnection and Microscale","STP","Hassler","What mechanisms lead to reconnection?\nWhat instabilities lead to global effects?\nWhat are the regions of particle acceleration? \nWhere are the reconnection regions and what is their topology? ","Mission Design\nSolar observations from single geosynchronous platform\nMission lifetime of 2 years\nPayload \nHigh Resolution EUV Imaging instrument\nEUV spectrograph\nX-ray calorimeter\nEUV Intermediate Scale Imager\n","Ultra-high resolution (0.02”/pixel) EUV coronal imaging\nHigh resolution (0.1”/pixel) EUV/UV spectroscopy\nX-ray Imaging Spectroscopy (1”/pixel; (E/DE) ~ 500 @ 1 keV) from 0.2 to 10 keV, with millisecond time resolution.\nMulti-wavelength EUV/UV intermediate scale imager (0.1”/pixel)\nHigh time resolution in all instruments\n","Enabling technology required - Large array, small pixel calorimeters for soft x-ray spectroscopy\nNew enhancing technology should reduce spacecraft cost by 10%\n",null,"MED",null,"Report 10/03"]
[0,10,10,0,5,0,10,7,5,5,0,7,7,null,"SCOPE","Solar Connection Observatory for Planetary Environments","OTHER ","Russell","Compare the global effects of external and internal driving mechanisms on planet and comet near-space environments through observations of auroral, airglow, coronal, and/or internal  plasma emissions\nDifferentiate features of Jupiter’s (and other giant planets’) auroral emissions due to internal processes (rotation and internal plasma sources) from those due to the solar wind interaction\nMeasure the response of ionosphere-solar wind coupling to changes in solar activity in planet systems without magnetospheres (Mars, Venus, Comets)\nRefine and expand our knowledge of Earth’s global geospace response by extending auroral observations into new domains of spatial and spectral resolution\nDirectly compare the terrestrial solar interaction with those of superior (Mars-Neptune) planets from  opposition campaigns that monitor both systems along the same Sun-planet line \nMap the opacity and velocity structure of the interplanetary hydrogen\nStudy the transition region between the heliosphere and LISM\nobservations. \nCompare Earth and other planets auroras.\nMeasurem interplanetary hydrogen.\nStudy transition from heliosphere to LISM. ","Dual meter-class telescopes (EUV & UV) covering bandpasses from 55 - 310 nm\nHubble Space Telescope (HST) - class performance for UV observations.  Highest sensitivity and spatial resolution yet achieved below 120 nm\nHigh (R<105) spectral resolution measurements of diffuse emissions with 50 times the etendue of HST-STIS.\nInner solar system observations of Venus, Mercury, and comets to within ~0.35 AU of the Sun\nL1-halo orbit for uninterrupted observations of the Earth’s North or South polar regions and a remote perspective on planets giving full hemisphere studies up to rotational poles.\n5+ years potential operational lifetime\n","Global imaging of auroral emissions, upper atmospheric circulation, exospheres and near-space plasma distributions\nImaging spectroscopy of UV ion-neutral emissions and atmospheric absorption features\nNarrow-field spectroscopy of planetary (auroral-dayglow-coronal) H Ly- profiles\nWide-field line profile measurements of diffuse H Ly- emission from the interplanetary medium (IPM), comets, geocorona,and the heliopause\nPencil-beam measurement of heliopause and LISM dynamics from H Ly- and H Ly- line-of-sight absorption spectroscopy \nHigh speed photon counting detectors for precision time resolution\nCoordinated SCOPE observations of planetary targets, the IPM and heliopause with existing in situ space probes\nCross-cutting techniques for characterizing auroral emissions in planetary magnetospheres, such as the development of auroral indices as a function of precipitating species at each of the planets (i.e., hemispheric power, auroral oval location, auroral oval size, etc.)\n","LLight-weight, metal-matrix-composite mirror design\nHigh- sensitivity/dynamic-range photon counting UV detectors\n"]
[3,10,10,0,7,0,10,10,3,7,0,5,10,null,"SEEC","Sun-Earth Energy Connector","LWS","Bailey","Quantify solar radiation and space weather:\nSpecify EUV radiation variability and source mechanisms.\nSimultaneously map neutral and plasma near-Earth environments.\nEstablish instantaneous relations among solar radiation, energetic precipitation, and space environment. ","MIDEX or STP class.\n3Re orbit, 50deg inclination.\nSimultaneous imaging of Sun's outer atmosphere and Earth's neutral atmosphere, day night atmosphere, and plasmasphere. ","EUV imaging of Sun and Earth.\nHigh resolution for local weather features.\nSolar EUV irradiance spectrum. \nLeads to development of new neutral gas and plasmasphere models. ","Ionospheric 91.1 nm imager\nOptics-free photoelectron spectrometer. ",null,"MED/SM"]
[10,10,{"$nulls":3},10,{"$nulls":4},10,10,null,null,"SEPP","Solar Energetic Particles Probe","MS05","Strachan","What are the source regions and physical processes controlling the impulsive and gradual production of solar energetic particles. \nTo understand how solar energetic particles (SEPs) are produced and accelerated in coronal mass ejection (CME) shocks.\n\nTo understand the role of flare/CME current sheets in the production of SEPs.\n\nTo understand the physical processes that control SEP production in compact magnetic field regions at the base of the corona.","A Near-Sun spacecraft (NSS) in a ~0.25 AU perihelion orbit and a Near-Earth spacecraft (NES) in a geosynchronous or sun synchronous orbit.\nLauncher: Single LV (e.g., Delta IV Heavy) with dual spacecraft\nNSS instruments: gamma-ray telescope, hard x-ray telescope, particles and magnetic field detectors, low frequency radio experiment \nNES instruments: EUV coronagraph/spectrometer, visible light coronagraph/polarimeter, and an EUV disk spectrometer.\n","The following measurements will determine the full range of parameters needed to test and refine all proposed theories for the production of impulsive and gradual SEPs:\nSEP production in CME shocks: \nSEP production in flare/CME current sheets: \nSEP production in compact magnetic field regions: ","   - ISP Development Funding",null,"LG/MED"]
[{"$nulls":14},"SHECon","Sun-Heliosphere-Earth Constellation","LWS","Roelof","Provide long-term relevant information on the Earth, Sun and its interconnecting medium as a system\nUnderstand, monitor and track the Sun, Earth and Heliosphere as a dynamic and evolving system\nProvide timely reports and predictions on the status and possible major disturbances in the Earth, Sun System\n","Establish an operational constellation of sensor suite(s) that satisfies the mission objectives\nDeploy sufficient sensors to measure the relevant data with adequate spatial and temporal and resolution\nImplement a data processing capability and information network to provide the required products and services\nRefresh, replace and enhance space borne constellation elements over time\nImprove modeling and algorithms as understanding and assets increase\n","Remote sensing of the Sun from locations needed to provide data for proven predictive models\nIn-situ sensors to measure key parameters in the Earth Sun interconnecting medium.\nNear Earth remote and in-situ measurements to complete and verify the monitoring and modeling of the Earth Sun System\n","Constellation suite(s) of sensors will all be developed and verified as roadmap missions are accomplished\nTechnology to integrate multiple data streams from multiple sources to provide timely operational results may be needed\n",null,"LG",null,"Obsolete?"]
[0,2,0,10,0,10,0,5,5,8,10,3,0,null,"SHIELDS","Solar Heliospheric and Interplanetary Environment Lookout in Deep Space","MS05","Liewer","Understand the observational requirements to achieve the space weather predictive capability necessary to enable NASA to assure safety for human and robotic exploration\n • Determine whether viewing active region evolution from 3 ecliptic vantage points spaced at 120 provides accurate forecasts of solar flares & “all clears”\n • Determine whether viewing CME eruptions from 3 vantage points spaced at 120 provides accurate forecasts of direction and velocity of large fast CMEs & associated SEP events\n • Determine whether magnetograms created from 3 vantage points spaced at 120 provides accurate boundary conditions for predictive models of space environment from Sun to Earth & Mars\n  Determine whether radio observations of CME shocks created from 3 vantage points spaced at 120 provides accurate identification of large fast CMEs\n"," • Two Spacecraft at  120 from Earth at 1 AU\n   - Also requires SC at Earth with similar instrumentation\n   - Launch with positive C3; on board propulsion for \n    stopping at   120 and for station keeping \n • Flight System Concept\n   - 3-axis stabilized platform with 30 arc-second pointing capability\n   - Payload: 26 kg, 24 W, 1.5 Mbps\n   - 30 arcsec (control), 15 arcsec (knowledge)\n"," • EUV Imaging of Sun for flare & CME detection\n • Filter Magnetograph for surface magnetic field measurements\n • Radio for CME shock detection\n • Coronagraph for CME detection and triangulation","TBD pending completion of mission study",null,"LG/MED"]
[{"$nulls":3},10,null,10,null,null,10,null,10,{"$nulls":3},"SI","Stellar Imager","VM","Strachan","Explore the patterns in surface magnetic fields throughout activity cycles on a substantial sample of stars like the Sun in order to develop and test a predictive dynamo model for the Sun.\nImage the evolving dynamo patterns on nearby stars by repeatedly observing them with ~1,000 resolution elements on their surface using UV emission as a proxy for magnetic field. \nImage the structure and differential rotation of stellar interiors by the asteroseismic technique of acoustic imaging, achieving 30 resolution elements on stellar disks with 1-min. time resolution in one or more broad optical pass bands. \n","Days to weeks of uninterrupted observing from a very stable environment, such as L2 \nStrategic mission, with 9 or more coordinated spacecraft\nMission lifetime: 5-10 years","Angular resolution of images better than 0.1 milli-arcsec\nReconfigure the imaging array fast enough to obtain images of stars within 1%  of their rotation period\nCompile at least ~20 images within a stellar rotation period to measure surface differential rotation and field evolution\nRevisit targets repeatedly during 3-6 month intervals over a period of 5-10 years. \nDetermine the interval structure and rotation with adequate resolution in layers where the dynamo operates\n",null,null,"LG",null,"Vision Mission"]
[{"$nulls":14},"SIRA","Solar Imaging Radio Array","MS05","Gopalswamy","• Enhance understanding of interplanetary propagation and evolution of coronal mass ejections (CMEs) using radio images of the CME-driven shock & other radio sources\n• Enhance understanding of solar energetic particle acceleration & propagation using images of fast-drift & other solar radio bursts\n• Apply above items to prediction of hazardous space weather\n• Obtain and analyze the 1st full-sky maps from 0.1 to 15 MHz\n","• Mission Design\n  - NASA MIDEX-class mission for aperture synthesis imaging\n  - Microsat constellation of 12-16 identical spacecraft\n  - Spherical constellation of 10 km diameter in L1 halo orbit\n  - Two high-heritage dipole antennas & radio receivers per µsat\n  - Direct downlink of data from each microsat to ground station \n• Flight System Concept\n  -  Carrier: 100 kg, 24 W; discarded after microsat deployment\n  -  Microsat: 54 kg (wet), 90 W, 8 Mbps downlink, ±1 deg (control)\n  -  V:  100 m/s (carrier), ~7 m/s (microsat) \n  -  Payload: 10 kg/sat (excluding timing and ranging), 10 W/sat\n","• Imaging at ~12 frequencies corresponding to ~2 RSUN – 1 AU\n• 2-bit Nyquist sampling at each frequency\n• ~2.4 GB science data/day/microsat\n•   “Snapshot” processing on ground for space weather prediction\nInstrument Summary \n•  Two 10 m crossed Stacer dipoles/µsat\n•  Two 0.03-15 MHz radio receivers/µsat\n•   Intersatellite transmissions for ranging, timing, and phase coherence, facilitated by long radio wavelengths (>20 m)","Low cost intersatellite ranging to 3 m is simple to build, but has not been tested ",null,"MED"]
[{"$nulls":14},"SO","Solar Orbiter","OTHER","Hassler","Fundamental physical processes of the solar atmosphere and heliosphere?\nLinks between solar corona and heliosphere?\nWhat are properties of plasma, fields, and particles in the near-Sun space?\nWhat is the fine scale structure and dynamics of the solar atmosphere and polar regions? ","ESA  mission: \n3x stabilized s/c, solar electric propulsion, multiple planetary swingbys. Perihelion 45 RS, at an orbital period of 149 days.\nMultiple VGAs to increase inclination to 30deg\nPerihelion hover period allows storm buildup imaging over several days. ","In situ solar wind analyzer, radio and plasma wave analyzer, magnetometer, energetic particles dust and neutral particle detectors, neutron detector.\nRemote: high res. EUV imager/spectrometer, visible light telescope and magnetograph, coronagraph, radiometer.\nCo-rotation and out of ecliptic observations. ","Solar electric propulsion from ESA SMART-1.\nHigh temperature thermal management to 25 1AU suns. ",null,"SM/MOO",null,"ESA Mission Report Fall 2004"]
[0,10,0,10,3,10,0,5,10,10,10,10,0,null,"SPI","Solar Polar Imager","VM ","Liewer","What is the relationship between the magnetism and dynamics of the Sun’s polar regions and the solar dynamo? \nWhat advantages does the polar perspective provide for space weather prediction? \nWhat is the azimuthal structure and dynamics of the corona and CMEs?\nHow are variations in the solar wind linked to the Sun at all latitudes?\nHow are solar energetic particles accelerated and transported in radius and latitude?\nHow does the solar irradiance vary with latitude?\n\n","SC in highly inclined ~75 3:1 resonant heliocentric 0.48 AU orbit\nUses solar sail to reach high inclination in 5-7 years\nCollect in situ data during cruise\nAverage data rate > 60 kbps; store and dump, 2 passes/week\nGimbaled antenna for uninterrupted helioseismology data\n\n","Surface & interior flows for helioseismology \nPolar magnetic fields and flux transport\nPolar coronal imaging in white light and EUV\nUV Spectrometer for outflow velocities\nIn situ magnetic fields, solar wind and energetic particles (SEPs)\n Total solar irradiance variability\n","Solar Sail Propulsion-Enabling\nLow mass/power Instrumentation\n",null,"MED",null,"VM : Report 2004"]
[{"$nulls":14},"SPP","Space Physics Package","MS05","Kletzing"," •  Fields, plasmas, particles environment measurement \n","Instrument Types\n Plasma Velocity Analyzer\n Energetic Particles Analyzer\n AC-DC Magnetometer, Plasma Wave Receiver\n Flight System Concept\nCost-effective modular and reconfigurable in-situ instrument suite for interplanetary and solar wind interactions with magnetospheres and ionospheres\nCommon CDH handles instrument data processing\nImplements centralized onboard decision making and intelligent data compression\n Near term implementation\nHeterogeneous instrument electrical interfaces accommodated via centralized flexible interfaces\n Intermediate/far term implementation\nInstruments adhere to selected standard electrical interfaces and protocols to facilitate “plug and play”\n permit reliable/flexible/low cost integration, test and software development\n","•   Support diverse missions with modular package","Radiation-hardened miniaturized, highly-integrated, low-power microelectronics  (Risk is contingent on continued ESMD ESR&T funding) ;Radiation-hardened power-efficient high-performance data processors (Risk is contingent on continued ESMD ESR&T funding);“Plug-and-play” instrument interfaces •Risk is low to moderate.  Requires use of standard interfaces and protocols; Miniature high-voltage power supplies•Risk is moderate.  No development funding in place ",null,"SM"]
[{"$nulls":14},"SWBs","Solar Weather Buoys","MS05","Roelof","Space Science:  Quantify and understand the global distribution of large solar disturbances that have propagated to ~1AU:  Solar Energetic Particle (SEP) events and Coronal Mass Ejections (CMEs). \nExploration:  SWBs will be a proof-of-concept for a warning system of radiation damage to space assets at Earth, Moon, Mars and in transit between these bodies\n","• Mission Design\n   - Lunar swingbys used to inject 12 to 15 small satellites into     a solar orbit of ~0.9 AU semi-major axis\n   - Launched in 2012 (TBD) on a Delta II\n   - Continuously monitor the environment for flares, SEPs     and CMEs\n • Flight System Concept\n   - Selected redundancy to achieve a 10-12 year mission life     (6-8 years to deploy all the satellites, 4 years of full      operations)\n   - Instrument Payload: 10 kg, 5 W,  ~10kb/day\n   - Attitude relative to the Sun: 10° control, 5° knowledge\n"," Energetic protons and electrons (solid-state detectors)\n - Fluence of 20-100 MeV protons\n - Onset of 100-300 keV electron beams (1 min resolution)\n Solar wind plasma (electrostatic)\n - Velocity, densitiy, temperature\n - CME velocities to 1500 km/s\nInterplanetary magnetic field (flux gate)\n - Vector components 0.1-100 nT\n - <1 min time resolution\nSolar hard x-rays (non-imaging spectrometer)\n - Flare timing (<1 minute) for identification\n -  Spectral hardness (20-80 keV)\n","Spacecraft deployment scenario:6 to 8 years for deployment; Spacecraft lifetime (8 to 10 years)",null,"MED/SM"]
[{"$nulls":14},"TE","Titan Explorer (2)","VM","TBD",{"$nulls":5},"LG",null,"VM (2) Reports"]
[{"$nulls":14},"TLM","Telemachus","STP","Roelof","• Understanding our changing Sun and its effects throughout the Solar   System (Space Science Enterprise Strategic Plan, November  2000)\n • Reveal through helioseismology how convection and rotation couple   and magnetic flux accumulates in the polar regions (solar dynamo)\n • Uncover the mechanism(s) in the polar regions of the Sun that    accelerate the solar wind and energetic particles and expel plasma    and magnetic fields (CMEs)\n • Exploit the polar viewpoint to examine the distribution of radio and x-  ray emission simultaneously from all solar longitudes\n • Determine the physics of the strongest stream/stream plasma    interactions and transient shocks where they are first formed in the    heliosphere\n"," • Example Mission Design\n   - Delta III Launch, 1765 kg @ C3 = 17 km2/s2 (12.7 min)\n   - VEEJGA Trajectory with Perihelion V\n     * 8.4 yr cruise, 3 yr science ops\n     * 0.2 x 2.5 AU Final Orbit, Period: 1.5 years\n   - 90 Heliographic Inclination\n     * 1st 4.5 years ecliptic (VEEJGA); 3 years In Final Orbit (polar)\n • Flight System Concept\n   - 3-Axis and Spin-Stabilized Platform\n   - Solar Arrays (Ultraflex, High Efficiency Silicon, High Temp Cells)\n   - Payload: 33 kg, 42 W, 8 kbps\n   - 2239 m/s V\n   - 30 arcsec (control), 10 arcsec (knowledge)\n"," • Continuous science except for 2 years beyond 3 AU (JGA)\n • Optimized Solar and heliospheric imagers (Doppler magnetograph,   two white light)\n • Basic, proven fast plasma, magnetic field and energetic particles in    situ detectors\n • Improved plasma elemental and isotopic composition for coronal    diagnostics and interstellar/cometary/”inner source” pickup ions\n • Sensitive radio directional spectrograph and x-ray spectrometer"," • High Temperature Solar Arrays\n • Dual Mode ACS (high precision 3-axis and F&P spin mode)",null,"MED",null,"Report 10/03"]
[null,null,10,null,null,10,10,null,10,null,10,{"$nulls":3},"TWINS","Two Wide-angle Imaging Neutral-atom Spectrometers ","MOO","Fennell",{"$nulls":3},"N/A",null,"SM/MOO",null,"Launch 2005"]
[null,null,10,10,{"$nulls":4},10,{"$nulls":3},10,null,"VAP","Venus Aeronomy Probe","OTHER","Moore"," • Determine Mechanisms for Energy Transfer From the Solar   Wind to the Ionosphere and Upper Atmosphere\n • Measure the Charged Particles Responsible for Auroral-Type   Emissions and Infer their Acceleration Mechanisms\n • Determine Formation Processes for Ionospheric Magnetic Flux    Ropes, Ionospheric “Holes” on the Nightside and the Loss of   Ionospheric Plasma in the Form of Streamers, Ray and Clouds\n"," • Example Mission Design\n   - Small Delta II\n   - 1-Year Flight Time, 1year OPS\n   - High Inclination Elliptical Orbit\n     * 150 km x 12,000 km \n • Flight System Concept\n   - Spin-Stabilized Platform\n   - Floating Potential Neutralization\n   - Solar Array Implementation\n"," • In-situ Plasma, Magnetic and Electric Fields and Plasma and   Radio Wave Measurements\n • In-situ Neutral Gas Composition, Density, Temperature, and   Winds Measurements\n • Remote Observations using a UV Spectral Imager, Fabry-Perot   Interferometer, Energetic Neutral Atom Imager,   Ionospheric Sounder","None enabling. Enhancing:\n • Low Mass/Power Instrumentation\n • Intelligent Instruments",{"$nulls":3},"variants studies at JPL"]
[]
[127,219,190,60,186,124,151,158,169,198,100,154,152]
["Notes: "]
["0. Cells can be expanded by clicking on them once or twice. "]
["1. Rows can be sorted or subsets selected using the pulldown menus for each column. "]
["2. POC is the person responsible for the Quad, and for weighting the RFA contributions (scale of 0-10). "]
["3. Roman numerals and letters refer to our Research Focus Areas, according to the definitions given below. "]
["4. Risk and Class are to be supplied as a result of our mission studies. Class is in units of MIDEXs. "]
["5. Status notes give the current status of mission studies. "]
["6. Link to Quad Charts and other mission data: http://sec.gsfc.nasa.gov/rdmteam/ or click link to right ->",{"$nulls":24},"Link to Quad charts and other mission data"]
["7. Mission cost classes:   MOO < SM < 500M$FY05 < MED < 1000M$FY05 < LG "]
[]
["Objectives and RFAs: "]
[null,"Opening the frontier to space environment prediction"]
["F","Understand the fundamental physical processes of the space environment – from the Sun to Earth, to other planets, and beyond to the interstellar medium."]
["F.1","Understand magnetic reconnection to reveal the causes of solar flares, coronal mass ejections, and geospace storms."]
["F.2","Understand the plasma processes that accelerate and transport particles "]
["F.3","Understand how nonlinear interactions transfer energy and momentum within planetary upper stmospheres."]
["F.4","Determine how solar and planetary magnetic dynamos are created and why they vary. "]
["F.5","Understand the role of cross-scale coupling in creating plasma boundaries and the  significance of boundaries in controlling physical processes"]
[null,"Understanding our home in space"]
["H","Understand how society, technological systems, and the habitability of planets are affected by the variable space environment."]
["H.1","Understand the causes and subsequent evolution of solar activity that affects Earth’s space climate and environment"]
["H.2","Determine changes in the Earth’s magnetosphere, ionosphere, and upper atmosphere to enable specification, prediction, and mitigation of their effects"]
["H.3","Understand the role of the Sun as an energy source to the Earth’s atmosphere, and in particular the role of solar variability in driving change. "]
["H.4","Apply our understanding of space plasma physics to the role of stellar activity and magnetic shielding in planetary system evolution and habitability"]
[null,"Safeguarding our outbound journey"]
["J","Maximize the productivity and safety of human and robotic explorers by developing predictive capability for the extreme and dynamic conditions in space."]
["J.1","Characterize the variability, extremes, and boundary conditions of the space environments that will be encountered by human and robotic explorers."]
["J.2","Develop the capability to predict the origin and onset of solar activity and disturbances associated with potentially hazardous space weather events."]
["J.3","Develop the capability to predict the propagation and evolution of solar disturbances to enable safe travel for human and robotic explorers."]
["J.4","Understand and characterize the space weather effects on and within planetary environments to minimize risk in exploration activities."]

{"sheet":"Mission Studies","index":1,"n_rows":63,"n_cols":10,"rows_kept":63,"merged":[[1,1,1,9],[3,0,3,9],[35,0,35,9],[58,2,58,8]],"headers":{"header":["","SEC Missions Study Status 07/21/04"]},"flags":["formulas_cached_only"]}
[]
[]
["SEC Missions Study Status","2000 RM Study","2003 RM Study","Inter-RM","Vision Mission","SDT","Pre-Form","Formulat","Implement","Comments"]
["Near-Intermediate"]
["STP Missions"]
["Solar-B",{"$nulls":7},"STP"]
["Solar-TERrestrial Relations Observatory (STEREO)",{"$nulls":7},"STP"]
["Magnetospheric Miultiscale (MMS) ",{"$nulls":5},"STP",null,null,"AO Phase 1 Selection"]
["Geospace Electrodynamics Connections (GEC)",{"$nulls":4},"STP",{"$nulls":3},"SDT Report"]
["Magnetsospheric Constellation (MC)",{"$nulls":4},"STP",{"$nulls":3},"Updated SDT In Process 2004"]
["Telemachus",null,"RM","IRM",{"$nulls":5},"Report 10/03"]
["Reconnection and Microscale (RAM)","RM","RM","IRM",{"$nulls":5},"Report 10/03"]
["Ionosphere Thermosphere Mesophere Waves Coupler","RM","RM"]
["Heliosperic Imager and Galactic Observer (HIGO)","RM","RM","IRM",{"$nulls":5},"Report 7/04"]
["LWS Missions"]
["Solar Dynamics Observatory (SDO)",{"$nulls":7},"LWS","(LWS)"]
["Geospace Storm Probes",{"$nulls":5},"LWS"]
["  - Ionosphere Thermosphere Storm Probes",{"$nulls":5},"LWS"]
["  - Radiation Belt Storm Probes",{"$nulls":5},"LWS"]
["Inner Heliosphere Sentinels (IHS)","RM","RM",null,null,"LWS",{"$nulls":3},"SDT Initiated 2004"]
["Inner Magnetospheric Constellation (IMC)","RM","RM","IRM",{"$nulls":5},"Report 6/03"]
["Tropical ITM Coupler","RM","RM"]
["Magnetic TRAnsition Region Probe (MTRAP)",null,"RM","IRM",{"$nulls":5},"Report Due 10/04"]
["Solar Probe",{"$nulls":4},"LWS",{"$nulls":3},"JPL/APL Reports; STDT initiated 3/04"]
["Explorers"]
["Coupled Ion Neutral Dynamics Investigation (CINDI)",{"$nulls":7},"EXP"]
["Two Wide-angle Imaging Neutral-atom Spectrometers (TWINS)",{"$nulls":7},"EXP"]
["Aeronomy of Ice in the Mesosphere (AIM)",{"$nulls":7},"EXP"]
["Time History of Events and Macroscale Interactions during Substorm (THEMIS)",{"$nulls":7},"EXP"]
["SSE/SEC Missions"]
["Jupiter Polar Orbiter (JPO)","RM","RM",{"$nulls":6},"New Frontiers Step 2- JUNO"]
["Io Electrodynamics","RM","Q"]
["Neptune Orbiter","Q","Q",null,"VM",{"$nulls":4},"Planetary with magnetospheric component"]
["Mars Aeronomy Probe","RM","Q",{"$nulls":6},"variants studies at JPL"]
["Venus Aeronomy Probe","RM",{"$nulls":7},"variants studies at JPL"]
["Long Term"]
["STP Missions"]
["Dayside Boundary Layer Constellation (DBC)","RM","Q"]
["Magnetosphere-Ionosphere Observatory (MIO)",null,"RM"]
["Particle Acceleration Solar Orbiter (PASO)","RM","RM"]
["Auroral Multi-Scale (AMS)",null,"RM"]
["Geospace System Response Imager (GSRI)","RM","RM"]
["Solar Connection Observatory for Planetary Environments (SCOPE)",null,"Q"]
["Solar Polar Imager","RM","RM","IRM","VM",{"$nulls":4},"Report 2003"]
["LWS Missions"]
["L1-Diamond",null,"RM","IRM",{"$nulls":5},"Report 10/04"]
["Solar Imaging Radio Array (SIRA)",null,"Q"]
["Sun-Earth Energy Connector (SEEC) ","RM"]
["Sun-Heliosphere-Earth Constellation",null,"Q"]
["Other Missions"]
["Bepi-Colombo",null,"RM",null,null,"SDT","YES","YES",null,"ESA AO Issued 4/04"]
["Interstellar Probe","RM","RM",null,"VM",{"$nulls":4},"2001-2 Reports"]
["Solar Orbiter",null,"Q",null,null,"SDT","YES",null,null,"ESA Mission Report Fall 2004"]
["Stellar Imager","Q","Q",null,"VM",{"$nulls":4},"Vision Mission"]
["Notes:"]
["Baseline = SEC 2003 Roadmap Appendix D Missions"]
["Q = Mission Quad Sheet Only"]
["RM = Roadmap Mission Team One Week Study "]
["IRM = HQ Selected Inter-Roadmap Studies w/IMDC/Team X"]
["VM = Visions Mission Under Study"]
["SDT = Science Definition Team Conducted with Program Mission Studies"]
["STP = Present Status in STP Program"]
["LWS = Present Status in LWS Program"]