National Aeronautics and Space Administration Goddard Space Flight

National Aeronautics and Space Administration Goddard Space Flight Center Goddard Space Jet Propulsion Laboratory Flight Center Jet Propulsion Laboratory Juno Mission Jack Connerney May 31, 2015 Launch Configuration Juno Spacecraft en route to Jupiter (Arrives July 4 th 2016) PI: Scott Bolton SWRI 05/31/2015 1

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Jupiter holds the secrets of solar system formation deep within the interior 05/31/2015 2

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory 05/31/2015 Galileo Probe – Where’s the Water? 3

Original Mission Plan Orbits

Revised Mission Plan Orbits View from Earth 14 day orbits 2 x 53 day orbits Sun Looking Down the North Pole

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno orbits over Jupiter’s poles and passes very close to the planet. Juno ducks under the hazardous radiation belts. Over time, radiation exposure increases. Orbits 1, 16 and 31 pictured 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno’s orbits are phased to envelope Jupiter in a dense mesh of potential field measurements - magnetic and gravity fields – to probe the deep interior. Juno will Earth-point on most periapsis passes for gravity measurements and re-orient slightly on others to optimize viewing for other instruments. 05/31/2015 7

Juno Spacecraft & Payload National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno. Cam UVS Waves SPACECRAFT DIMENSIONS Diameter: 66 feet (20 meters) Height: 15 feet (4. 5 meters) JEDI JIRAM (6 sensors ) (2 detectors) JADE (4 sensors ) Gravity Science (2 sensors) Magnetometer (2 MAG sensors, 4 star cameras) MWR (6 sensors ) Scott Bolton 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Mission Context (400 days ‘till JOI) Juno today (L+1395) JUPITER 3 01 , 2 9 t Oc Aug 11, 2011 EFB main asteroid belt CERES MARS EARTH VENUS 05/31/2015 9

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Probing Deep and Globally Juno probes deep into Jupiter in three ways: Spacecraft tracks • Microwave radiometry probes deep into the meteorological layer • Magnetic fields probe into dynamo region of metallic hydrogen layer • Gravity fields probe into central core region Along-track scanning 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Microwave Radiometer (MWR) The microwave antennas are distributed around the spacecraft and view perpendicular to the spacecraft spin axis Spacecraft tracks 120° Field of View A 6: horn off-nadir view emission angle nadir view A 2: patch array A 1: patch array A 3 - A 5: slot arrays Along-track scanning 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Microwave Sounding 12° footprints (1. 37 – 11. 55 cm) 20° footprints (24, 50 cm) Weighting functions: Measurement wavelengths sample atmosphere from cloud tops to >> 100 bar. 05/31/2015 Footprints: atmosphere densely sampled along sub-spacecraft track. 12º and 20° footprints are displaced for clarity. Only 1 of every 1200 footprints is shown.

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Mapping Jupiter’s gravity Ka-band radio system (32 -34 GHz) • • • High eccentricity orbits Period: 14 days 6 h tracking at Ka band Periapsis altitude ~ 5000 km Range rate accuracy 3 x 10 -6 m/s @ 1000 s integration 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Gravity Investigation • 25 (24) gravity passes anticipated at this time • Gravity science also available during MWR passes • Orbit close to face-on (20º) initially (periapsis near dusk) 05/31/2015 14

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory 05/31/2015 Juno Gravity Investigation 15

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Jupiter’s “Surface” Gravity Shallow winds (H = 300 km) (0. 15 m. Gal) Deep winds (H = 3000 km) (8 m. Gal) Gravity field accuracy is ~ 0. 2 m. Gal at best, increasing up to 30 m. Gal in the polar regions 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno MAG Instrument Suite Optical Cube ASC CHUs CSi. C MOB FGM Sensor CHU Inner Light Baffles FGM Sensor ASC = Advanced Stellar Compass CHU = Camera Head Unit FGM = Fluxgate Magnetometer 05/31/2015 Two Identical MAG Optical Bench (MOB) Assemblies populate the MAG Boom, one In. Board (IB), one Out. Board (OB) @ 10, 12 m.

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Magnetometer Suite Magnetic Observatory Characteristics Sensors Type: Dual Tri-axial Ring Core Fluxgates, each with two co-located Non-Magnetic Star Cameras Dynamic Ranges & (resolution) Range 6: Range 5: Range 4: Range 2: Range 1: Range 0: 16. 384 G (+/- 25. n. T) 4. 0960 G (+/- 6. 25 n. T) 1. 0240 G (+/- 1. 56 n. T) 0. 2560 G (+/- 0. 39 n. T) 0. 0640 G (+/- 0. 19 n. T) 0. 0160 G (+/- 0. 05 n. T) FGM Vector Accuracy: ~0. 01% of full scale FGM Intrinsic Noise Level: << 1 n. T FGM Zero Level Stability: < 1 n. T Spacecraft Magnetic Cleanliness: < 2 n. T Static and < 0. 5 n. T Dynamic Intrinsic FGM Sample Rate: 64 Vector Samples/Second Advanced Stellar Compass: Four Camera Head Units (CHUs), CCD Imager Attitude Determination Accuracy: ~10 Arcsec (spin rate dependent) Attitude Solution Rate: 4 Quaternions per second 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory MAG Science Objectives Magnetic Spectra • Characterize Jovian internal field to spherical harmonics n > 14, and provide unprecedented resolution of the dynamo process. • Explores polar magnetosphere. • ∆B measures Birkeland currents as Juno passes through auroral oval. • Provides vector B to payload.

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Jovian Auroral Dynamics Experiment 3 JADE-Electron Sensors JADE-Ion Sensor JADE Central Electronics Unit 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory JADE Measurements Summary JADE-E (3 Sensors) JADE-I 100 e. V – 100 ke. V 10 e. V/q – 50 ke. V/q 10 -14% (depends on E) 18 -28% (depends on E) 360°x 3 -6° 270°x 8. 5° Uses 1 s MAG data - 3 Sensors x 16 / 7. 5° 12 / 22. 5° Mass Range - 1 - 64 amu M/DM - 2. 5 – 11 (depends on M & E) ~2 -5 x 10 -5 cm 2 sr e. V/e. V ~4 x 10 -5 cm 2 sr e. V/e. V Full PAD each 1 s 4 p each 30 s spin Energy Range E/E FOV (Inst) FOV Tracking Pixels/Res G factor/pixel Time Res 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory JADE Science Objectives • Explore polar magnetosphere, auroral region electrons & ions • Characterize precipitating particle distributions that drive auroral emissions • Identify particle acceleration processes • Examine composition and mass loading from satellites • Observe plasma disk, middle magnetosphere; address structure & evolution • Collaborative studies with other Juno measurements 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Energetic Particle Detectors JEDI 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Energetic Particle Detectors Three Juno Energetic Particle Detector Instruments (JEDI) measure energetic electrons and ions that help cause Jupiter’s aurora Parameter Capability Comment 25 – 1000 ke. V Abuts JADE H+: 15 -10000 ke. V He: 25 -10000 O/S+: 40 -100000 ke. V Abuts JADE 25% Earth Aurora Spectra Driver Angle Resolution 18° using rotation <= 30 km Auroral Sampling / Pitch Angle (PA) Coverage 0 -360 degrees for whole Orbit Resolve loss cone R < 3 RJ / Ion composition H above 10 ke. V He above 50 ke. V O Above 45 ke. V Separate S from O for E > 200 ke. V Electron Energies Ion Energies Time Sampling 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno’s Unique Location Juno flies through the auroral acceleration region; JEDI characterizes: particle precipitation, heating and ionization in the upper atmosphere and signatures of the structure of Jupiter’s polar space environment. Is downward acceleration (to 500 ke. V at Jupiter) coherent (like Earth) or diffuse? What is the role of acceleration in global auroral current systems? Enough precipitating heavy ions (many MEV) to explain auroral X-ray emissions? 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Waves Overview Search Coil Preamps & Electronics 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno Waves Instrument Characteristics Spectral Coverage: 50 Hz – 20 k. Hz Magnetic 50 Hz – 40 MHz Electric Spectral Resolution: ~20 Channels/decade Periapsis Mode Cadence: 1 spectrum/second LF and MF Burst Modes: Waveform Captures in all bands to 150 k. Hz triggered onboard HF Burst Modes: Ability to select a 1 -MHz band including fce 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Waves Science Objectives • Explore radio and plasma waves in the polar magnetosphere • Examine the role of plasma waves in the auroral acceleration region • Identify and observe in-situ source regions of Jovian radio emissions • Additional Science Objectives: > Observe the structure and dynamics of the plasmasheet > Monitor radio emissions as a proxy for magnetospheric dynamics > Measure dust impacts between the ring system and the atmosphere

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno UVS Overview Telescope/Spectrograph Off-axis Primary Mirror Detector Electronics XDL Detector Assembly Slit Assembly Grating Aperture Door -30º Projection of UVS slit on sky 0º +30º Entrance Baffle Scan Mirror Assembly Scan Mirror Rotation Axis

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno UVS Performance Feature Characteristic or Performance Driving Requirement Spectral Range: 70 -205 nm 78 -172 nm (H 2 & H emissions) Spectral Resolution ~0. 4 0. 6 nm (point source); ~1. 0 2. 6 nm (extended) <3 nm filled slit (color ratio) Spatial Resolution 0. 1° (125 km from 1 RJ above the aurora) <500 km (HST-like spectral imaging) Effective Area: 0. 002 cm 2 @ 105 nm, 0. 02 cm 2 @ 170 nm >100 k. R (moderately bright auroras) IFOV: 0. 2° x 2. 5° + 0. 025° x 2° + 0. 2° x 2. 5° → “dog-bone” shape Field of Regard: 360° x 60° (2 RPM & ± 30° from spin plane → half the sky is accessible) Detector Type: Curved 2 -D MCP (solar blind), Csl photocathode, cross delay-line (XDL) readout, 24 bits/event; 2048 spectral (perpendicular to slit) x 256 spatial (parallel to slit) x 32 (PHD)

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno UVS - Jovian Aurora • Imaging and spectroscopy of UV HST FUV Image auroral emissions: Ø Imaging auroral morphology, mapping emission to provide context for in-situ particles and fields measurements Ø Spectroscopy to determine the mean energy of precipitating electrons Clarke et al. 2002 Ø Magnetic field models map from Juno s/c to polar field UV Auroral Emissions: line footprint – H 2 Lyman Bands (80 -170 nm) ~40% • Additional Science Objectives: – H 2 Werner Bands (80 -130 nm) ~40% – H 2 Rydberg Bands (80 -90 nm) ~5% – H Lyman series (121. 6 nm, etc. ) ~15% Ø Observe the S/C footprint region to compare UVS data with particle & waves data Ø Look for structure & variability in low-latitude airglow emissions Ø Determine auroral-region atmospheric composition using reflected sunlight 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Jovian Infra. Red Auroral Mapper Juno – JIRAM Focal Planes Assembly Scanning Concept Optical Head 32

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Jovian Infra. Red Auroral Mapper • JIRAM is both an imager and a spectrometer. • Heritage from: Cassini, Venus Express, Dawn and Rosetta. • The spectrometer operates in the spectral range 2 -5 µm (resolution of 9 nm). • The imager has two contiguous channels at 3. 3 -3. 6 µm for auroras and at 4. 5 -5. 0 µm for Jovian thermal emission. • H 3+ has strong emissions throughout JIRAM’s spectral range. 33

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Jovian Infra. Red Auroral Mapper JIRAM maps Jovian aurorae at infrared wavelengths emitted by H 3+. This ion is formed at the base of the exosphere through the reaction H 2+ + H 2 H 3+ + H. JIRAM will visualize Jovian infrared auroral emissions in conjunction with ultraviolet auroral emissions observed by Juno’s UVS. NADIR and limb observations with JIRAM’s spectrometer measures temperature and concentrations of emitting ions. HST/STISS UV Image IRTF/NSFCAM H 3+ Image 12: 26 UT 12: 24 UT December 16, 2000 (UT) Observations 34

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno. Cam • Juno. Cam was conceived as a small EPO camera but it does enjoy unique polar views • Camera designed for optimum performance when Juno has best polar views Science Objectives • Polar meteorological phenomena • Observe small-scale structure of storms (resolution 10 x better than previous missions) • Provide context for data from deeper in the atmosphere (JIRAM and MWR) 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno. Cam • Juno. Cam is a heritage design of the Mars Science Laboratory (MSL) rover Mars Descent Imager (MARDI) with limited modifications, built by Malin Space Science Systems • 1600 pixel, 58º wide FOV • Juno. Cam is a fixed field of view push-frame visible camera that images in four color bands: Blue, green, red, and Methane band. • Uses time-delay integration (TDI) on spinning spacecraft to increase signal-to-noise ratio (snr). 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Juno. Cam Outreach • Engage the public – Provide insight into the scientific planning process, factors that influence scientific decisions • Rely on amateur astronomers to supply images of Jupiter for planning purposes • Include college students in the outreach effort and blogs • Include public in target selection • Image processing community will produce color images, movies, etc. – demonstrated at earth flyby 05/31/2015

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory 05/31/2015 38

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory 05/31/2015 Juno EFB Overview 39

National Aeronautics and Space Administration Goddard Space Flight Center Jet Propulsion Laboratory Earth and Moon As seen by the Juno spacecraft en route to Jupiter October 9 th 2013 J L Joergensen et al. Technical University of Denmark 05/31/2015 40