PDS_VERSION_ID = PDS3 RECORD_TYPE = STREAM LABEL_REVISION_NOTE = " 2012-03-12 JUNO: Kurth Revision 1; 2015-08-15 JUNO: Kurth and Stephens Revision 2; 2016-10-13 PDS: Mafi Revision 3; 2017-04-20 JUNO: Kurth Revision 4;" OBJECT = MISSION MISSION_NAME = "JUNO" OBJECT = MISSION_INFORMATION MISSION_START_DATE = 2011-08-05 MISSION_STOP_DATE = NULL MISSION_ALIAS_NAME = NULL MISSION_DESC = "The majority of the text in this file was extracted from the Juno Mission Plan Document, S. Stephens, 29 March 2011.[JPL D-35556] Mission Overview ================ Juno launched on 5 August 2011. The spacecraft uses a deltaV-EGA trajectory consisting of a two part deep space maneuver on 30 August and 14 September 2012 followed by an Earth gravity assist on 9 October 2013 at an altitude of 559 km. Jupiter arrival is on 5 July 2016 commencing operations for a 5 (Earth) year-long prime mission comprising 32 high inclination, high eccentricity orbits of Jupiter. The orbit is polar (90 degree inclination) with a periapsis altitude of 4200-8000 km and a semi-major axis of 56.35 RJ (Jovian radius) giving an orbital period of 52.83 days. The primary science is acquired for approximately 12 hours centered on each periapsis although fields and particles data are acquired at low rates for the remaining apoapsis portion of each orbit. Currently, 5 of the first 7 periapses are dedicated to microwave radiometry of Jupiter's deep atmosphere with most of the remaining orbits dedicated to gravity measurements to determine the structure of Jupiter's interior. All orbits will include fields and particles measurements of the planet's auroral regions. Juno is spin stabilized with a rotation rate of 2 rotations per minute (RPM). For the radiometry orbits the spin axis is precisely perpendicular to the orbit plane so that the radiometer fields of view pass through the nadir. For gravity passes, the spin axis is aligned to the Earth direction, allowing for Doppler measurements through the periapsis portion of the orbit. The orbit plane is initially very close to perpendicular to the Sun-Jupiter line and evolves over the 5-year mission. Generally, data acquired during the periapsis passes are recorded and played back over the subsequent apoapsis portion of the orbit, although some data can be downlinked during the gravity passes. Juno's instrument complement includes Gravity Science using the X and Ka bands to determine the structure of Jupiter's interior; magnetometer investigation (MAG) to study the magnetic dynamo and interior of Jupiter as well as to explore the polar magnetosphere; and a microwave radiometer (MWR) experiment covering 6 wavelengths between 1.3 and 50 cm to perform deep atmospheric sounding and composition measurements. The instrument complement also includes a suite of fields and particle instruments to study the polar magnetosphere and Jupiter's aurora. This suite includes an energetic particle detector (JEDI), a Jovian auroral (plasma) distributions experiment (JADE), a radio and plasma wave instrument (Waves), an ultraviolet spectrometer (UVS), and a Jupiter infrared auroral mapping instrument (JIRAM). The JunoCam is a camera included for education and public outreach. While this is not a science instrument, we plan to capture the data and archive them in the PDS along with the other mission data. The MAG investigation consists of redundant flux gate magnetometers (FGM) and co-located advanced stellar compasses (ASC). The ASCs are provided by the Danish Technical University under an effort led by John Jorgenson. Scott Bolton is the Juno Principal Investigator. The Science Team members responsible for the delivery and operation of the instruments are listed below: Instrument Acronym Lead Co-I ---------------------------------------------- -------- --------- Gravity Science GRAV Folkner Magnetometer MAG Connerney Microwave Radiometer MWR Janssen Jupiter Energetic Particle Detector Instrument JEDI Mauk Jovian Auroral Distributions Experiment JADE McComas Radio and plasma wave instrument Waves Kurth Ultraviolet Imaging Spectrograph UVS Gladstone Jovian Infrared Auroral Mapper JIRAM Adriani Juno color, visible-light camera JUNOCAM Hansen Mission Phases ============== LAUNCH ------ The Launch phase starts at L-40 min (Launch-40 min), and covers the interval from launch, through initial ground station acquisition, until the establishment of a pre-defined, stable, and slowly changing Sun- pointed attitude when cruise attitude control algorithms and ephemerides can be used. The end of the Launch phase is determined by post-launch health and safety assessments. The boundary is at L+3 days, after initial acquisition and after confirmation that the Flight System is safe and in a power-positive, thermally stable, and commandable attitude. Target Name : N/A Mission Phase Start Time : 2011-08-05 (2011-217) Mission Phase Stop Time : 2011-08-08 (2011-220) INNER CRUISE 1 -------------- The Inner Cruise 1 phase lasts from post-Launch establishment of a pre-defined and stable Sun-pointed attitude when cruise attitude control algorithms and ephemerides can be used, until after initial spacecraft and instrument checkouts have been performed and the spacecraft has gotten far enough from the Sun to allow Earth-pointing instead of Sun-pointing. TCM 1 (the first planned trajectory correction maneuver) was deemed not necessary, hence, was not executed. The phase spans the interval from L+3 to L+66 days. Target Name : SOLAR_SYSTEM Mission Phase Start Time : 2011-08-08 (2011-220) Mission Phase Stop Time : 2011-10-10 (2011-283) INNER CRUISE 2 -------------- The Inner Cruise 2 phase spans the period from L+66 days until L+663 days. The Deep Space Maneuvers (DSMs) occur during this phase, near aphelion of Juno's first orbit about the Sun, on the way to Earth Flyby and then Jupiter. There is increased DSN (Deep Space Network) coverage associated with the DSMs and a cleanup TCM. DSMs 1 and 2 occur on 2012-08-30 and 2010-09-14. Target Name : SOLAR_SYSTEM Mission Phase Start Time : 2011-10-10 (2011-283) Mission Phase Stop Time : 2013-05-29 (2013-149) INNER CRUISE 3 -------------- The Inner Cruise 3 phase spans the interval from L+663 days to L+823 days. The duration of this cruise phase is 160 days. Featured in this phase is Earth Flyby (EFB), which gives Juno a gravity assist (providing 7.3 km/s of deltaV) on its way to Jupiter. It occurs as the spacecraft is completing one elliptical orbit around the Sun and includes perihelion. Three TCMs were planned before EFB (the last of which was deemed not necessary) and one after EFB. There is increased DSN coverage associated with the 4 maneuvers and EFB. The Inner Cruise 3 phase is focused on performing the required maneuvers, as well as an integrated operations exercise around Earth Flyby, subject to Flight System constraints. Closest approach to Earth occurs on 2013-10-09 at 19:21 UTC. Target Name : EARTH, SOLAR_SYSTEM Mission Phase Start Time : 2013-05-29 (2013-149) Mission Phase Stop Time : 2013-11-05 (2013-309) Earth Closest Approach : 2013-10-09T19:21 (2013-282) OUTER CRUISE ------------ The Outer Cruise phase lasts from L+823 days until the start of Jupiter Approach at Jupiter Orbit Insertion (JOI)-6 months (JOI-182 days or L+1614 days). The duration of this cruise phase is 791 days, which is over 2 years. Target Name : SOLAR_SYSTEM Mission Phase Start Time : 2013-11-05 (2013-309) Mission Phase Stop Time : 2016-01-05 (2016-005) JUPITER APPROACH ---------------- The Jupiter Approach phase lasts the final 6 months of cruise before Jupiter Orbit Insertion and is an opportunity for final Flight System and instrument checkouts as well as science observations to start exercising the ground system and Flight System, although orbit insertion preparations limit instrument activities close to JOI. There are more frequent maneuvers approaching JOI, starting with a TCM at JOI-5 months, and correspondingly increasing DSN coverage. The 178-day Jupiter Approach phase is preceded by a 26-month Outer Cruise phase. Jupiter Approach starts 3 months after the project is fully staffed up in preparation for JOI and the 1.3 years of science orbits. The phase ends at JOI-4 days, which is the start of the JOI critical sequence. Target Name: : JUPITER, SOLAR_SYSTEM Mission Phase Start Time : 2016-01-05 (2016-005) Mission Phase Stop Time : 2016-07-01 (2016-183) JUPITER ORBIT INSERTION ----------------------- The JOI phase encompasses the JOI critical sequence. It begins 4 days before the start of the orbit insertion maneuver and ends 1 hour after the start. JOI, the second critical event of the mission, occurs at closest approach to Jupiter, and slows the spacecraft enough to let it be captured by Jupiter into a 53.8-day orbit. A cleanup burn at JOI+8.6d during the Capture Orbits phase is required to clean up JOI maneuver execution errors. DSN coverage is continuous during the JOI phase. Target Name : N/A Mission Phase Start Time : 2016-07-01 (2016-183) Mission Phase Stop Time : 2016-07-05 (2016-187) Perijove 0 : 2016-07-05T02:47:32 (2016-187) SCIENCE ORBITS -------------- The Science Orbits phase includes Orbit 0 through Orbit 35. Orbit N is defined from apojove (AJ) N-1 through apojove N, and includes perijove (PJ) N. Orbit numbering starts before the Science Orbits phase. JOI occurs at PJ0, so Orbit 0 lasts from PJ0 through AJ0 (including a JOI cleanup maneuver at JOI+8.6d). Orbit 1 includes PJ1, and runs from AJ0 through AJ1. Orbit 2 includes PJ2, and runs from AJ1 through AJ2. Orbit 3 includes PJ3, and runs from AJ2 through AJ3. Early orbital science is baselined in Orbits 0, 1, 2, and 3, except for the JOI keepout zone. Orbit 4 is the first science orbit. It includes PJ4 (and the first OTM at PJ4+7.5h), and runs from AJ3 through AJ4. The last science orbit is Orbit 34. It is bookkept as an extra science orbit, since the mission uses Orbits 2 through 33 to obtain 32 perijoves with MAG and other data that meet Level-1 baseline science requirements. Small (up to 8 m/s) orbit trim maneuvers (OTMs) are planned after each set of perijove science observations, at PJ+4h, PJ+6h, or PJ+7.5h in Orbits 4 through 34, to target the perijove longitude required for science observations in the next orbit. There is no need for an OTM after PJ34. A deorbit maneuver (deterministic deltaV = 77 m/s) is planned near AJ34. Radiation accumulation increases substantially as the orbital line of apsides rotates and perijove latitude increases from 3 degrees at JOI to 36 (TBD) degrees at PJ35. There are currently no plans for an extended mission. Target Name : JUPITER Mission Phase Start Time : 2016-07-05 (2016-187) Mission Phase Stop Time : 2021-07-03 (2021-184) Perijove 1 : 2016-08-27T12:50:44 (2016-240) Perijove 2 : 2016-10-19T18:10:54 (2016-293) Perijove 3 : 2016-12-11T17:03:41 (2016-346) Perijove 4 : 2017-02-02T12:57:09 (2017-033) Perijove 5 : 2017-03-27T08:51:52 (2017-086) Perijove 6 : 2017-05-19T06:00:45 (2017-139) Perijove 7 : 2017-07-11T01:54:51 (2017-192) Perijove 8 : 2017-09-01T21:48:57 (2017-244) Perijove 9 : 2017-10-24T17:43:00 (2017-297) Perijove 10 : 2017-12-16T17:57:39 (2017-350) Perijove 11 : 2018-02-07T13:51:49 (2018-038) Perijove 12 : 2018-04-01T09:45:57 (2018-091) Perijove 13 : 2018-05-24T05:40:07 (2018-144) Perijove 14 : 2018-07-16T05:17:38 (2018-197) Perijove 15 : 2018-09-07T01:11:55 (2018-250) Perijove 16 : 2018-10-29T21:06:15 (2018-302) Perijove 17 : 2018-12-21T17:00:25 (2018-355) Perijove 18 : 2019-02-12T16:19:48 (2019-043) Perijove 19 : 2019-04-06T12:13:58 (2019-096) Perijove 20 : 2019-05-29T08:08:13 (2019-149) Perijove 21 : 2019-07-21T04:02:44 (2019-202) Perijove 22 : 2019-09-12T03:40:47 (2019-254) Perijove 23 : 2019-11-03T23:32:56 (2019-307) Perijove 24 : 2019-12-26T16:58:59 (2019-360) Perijove 25 : 2020-02-17T17:51:36 (2020-048) Perijove 26 : 2020-04-10T14:24:34 (2020-101) Perijove 27 : 2020-06-02T10:19:55 (2020-154) Perijove 28 : 2020-07-25T06:15:21 (2020-207) Perijove 29 : 2020-09-16T02:10:49 (2020-260) Perijove 30 : 2020-11-08T01:49:39 (2020-313) Perijove 31 : 2020-12-30T21:45:12 (2020-365) Perijove 32 : 2021-02-21T17:40:31 (2021-052) Perijove 33 : 2021-04-15T13:36:26 (2021-105) Perijove 34 : 2021-06-07T09:32:03 (2021-158) DEORBIT ------- The Deorbit phase occurs during the final perijove-to-perijove orbit of the mission. The 7-day phase starts several days after the Orbit 34 perijove science pass (part of the extra orbit) at AJ34-1h, before the start of the apojove deorbit maneuver (by which time we hope to have all or most of the PJ34 data on the ground). It continues through AJ34, and ends with Impact into Jupiter at PJ35. In order to meet planetary protection requirements and ensure that we do not impact Europa (as well as Ganymede and Callisto), the spacecraft performs a deorbit maneuver near apojove that reduces our orbital velocity and sends us to a perijove below Jupiter's cloud tops. The mean burn deltaV of 77 m/s is the largest maneuver of the mission after the 3 main engine maneuvers, and is planned to be performed on RCS (Reaction Control System) thrusters (deltaV to Earth angle, ELA ~ 70 degrees). The timing of the burn is not mission critical; a contingency delayed execution can occur several days around and following apojove if necessary. Impact into Jupiter marks End of Mission (EOM). Target Name : JUPITER Mission Phase Start Time : 2021-07-03 (2021-184) Mission Phase Stop Time : 2021-07-31 (2021-212) Perijove 35 : 2021-07-30T04:33:28 (2021-211) " MISSION_OBJECTIVES_SUMMARY = " JUNO MISSION OBJECTIVES ======================= Juno's science objectives encompass four scientific themes: origin, interior structure, atmospheric composition and dynamics, and polar magnetosphere. These are based on Appendix E to the New Frontiers Program Plan: Program Level Requirements for the Juno Project (PLRA). Juno addresses science objectives central to three NASA Science divisions: Solar System (Planetary), Earth-Sun System (Heliophysics), and Universe (Astrophysics). Juno's primary science goal of understanding the formation, evolution, and structure of Jupiter is directly related to the conditions in the early solar system which led to the formation of our planetary system. The mass of Jupiter's solid core and the abundance of heavy elements in the atmosphere discriminate among models for giant planet formation. Juno constrains the core mass by mapping the gravitational field, and measures through microwave sounding the global abundances of oxygen (water) and nitrogen (ammonia). Juno reveals the history of Jupiter by mapping the gravitational and magnetic fields with sufficient resolution to constrain Jupiter's interior structure, the source region of the magnetic field, and the nature of deep convection. By sounding deep into Jupiter's atmosphere, Juno determines to what depth the belts and zones penetrate. Juno provides the first survey and exploration of the three-dimensional structure of Jupiter's polar magnetosphere. The overall goal of the Juno mission is to improve our understanding of the solar system by understanding the origin and evolution of Jupiter. ATMOSPHERIC COMPOSITION ----------------------- Juno investigates the formation and origin of Jupiter's atmosphere and the potential migration of planets through the measurement of Jupiter's global abundance of oxygen (water) and nitrogen (ammonia). a) Measure the global O/H ratio (water abundance) in Jupiter's atmosphere. b) Measure the global N/H ratio (ammonia) in Jupiter's atmosphere. ATMOSPHERIC STRUCTURE --------------------- Juno investigates variations in Jupiter's deep atmosphere related to meteorology, composition, temperature profiles, cloud opacity, and atmospheric dynamics. a) Determine microwave opacity as a function of latitude and altitude (pressure). b) Determine depths of cloud and atmospheric features such as zones, belts, and spots, and map dynamical variations in ammonia and water. c) Characterize microwave opacity of the polar atmosphere region. MAGNETIC FIELD -------------- Juno investigates the fine structure of Jupiter's magnetic field, providing information on its internal structure and the nature of the dynamo. a) Map the magnetic field of Jupiter, globally, by direct measurement of the field at close-in radial distances. b) Determine the magnetic spectrum of the field, providing information on the dynamo core radius. c) Investigate secular variations (long-term time variability) of the magnetic field. GRAVITY FIELD -------------- Juno gravity sounding explores the distribution of mass inside the planet. a) Determine the gravity field to provide constraints on the mass of the core. b) Determine the gravity field to detect the centrifugal response of the planet to its own differential rotation (winds) at depths of kilobars and greater. c) Investigate the response to tides raised by the Jovian satellites. POLAR MAGNETOSPHERE ------------------- Juno explores Jupiter's three-dimensional polar magnetosphere and aurorae. a) Investigate the primary auroral processes responsible for particle acceleration. b) Characterize the field-aligned currents that transfer angular momentum from Jupiter to its magnetosphere. c) Identify and characterize auroral radio and plasma wave emissions associated with particle acceleration. d) Characterize the nature, location, and spatial scale of auroral features. " END_OBJECT = MISSION_INFORMATION OBJECT = MISSION_HOST INSTRUMENT_HOST_ID = "JNO" OBJECT = MISSION_TARGET TARGET_NAME = "CALLISTO" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "DUST" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "EARTH" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "EUROPA" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "GANYMEDE" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "IO" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "IO PLASMA TORUS" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "JUPITER" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "MOON" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "J RINGS" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "SOLAR WIND" END_OBJECT = MISSION_TARGET OBJECT = MISSION_TARGET TARGET_NAME = "SOLAR_SYSTEM" END_OBJECT = MISSION_TARGET END_OBJECT = MISSION_HOST OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "JPLD-35556" END_OBJECT = MISSION_REFERENCE_INFORMATION END_OBJECT = MISSION END