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From page 633... ...
In developing the lists of mission concepts to provide to the steering committee, each of the science study panels -- the Panel on Physics of Ionospheres, Thermospheres, and Mesospheres; the Panel on the Physics of Magnetospheres; and the Panel on Physics of the Sun and Heliosphere -- began with the identification of priorities for solar and space physics science. This identification was informed by literature reviews, feedback from community meetings and workshops, and especially responses from a request for information.2 In response to this request, the panels received 450 community input papers.
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From page 634... ...
G.2 SYNOPSIS OF TRACE RESULTS G.2.1 The Selected Mission Concepts As noted above, the steering committee selected 12 mission concepts for the full TRACE process and an additional one that went through the technical and risk assessment but not the cost assessment: • Multipoint Comprehensive Eruptive Mission (MCEM) • Ecliptic Heliospheric Constellation (ECH)
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From page 635... ...
• B us: 50 year life, 7 54 kg dry mass • H eliocentric escape Launch: SLS B lock 2, Centaur U/S, STAR 48B V 1 FIGURE G-1 Notional Sun and heliosphere mission concepts evaluated using technical, risk, and cost evaluation (Clockwise from Top Left) : MCEM (Multipoint Comprehensive Eruptive Mission)
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From page 636... ...
B us • 3-year life spacecraft, S-band communications, hydraz ine propulsion system, 3-axis stabiliz ed, powered body mounted 9 .5 m2 cylindrical solar array and 26 Ah Li Ion battery Launch: Minotaur-C (evolved Taurus) , nominal launch years: 2030, 2032, 2035 2 FIGURE G-2 Notional ionosphere, thermosphere, mesosphere concepts evaluated using technical, risk, and cost evaluation (Clockwise from the Top Left)
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From page 637... ...
, and Links: Links between regions and scales in geospace. NOTE: API, Auroral Plasma Instrument; CDS, charge discharge sensor; CPA, Core Plasma Analyzer; DES, Dual Electron Spectrometer; EFI, Electromagnetic Fields Instrument; ENA, energetic neutral atom; ESA, electrostatic analyzer; EUV, extreme ultraviolet; GCI, Geocoronal Imager; HPCA, Hot Plasma Composition Analyzer; MAG, magnetometer; MagCon, magnetospheric constellation; PARAGON, Plasma Acceleration, Reconfiguration, and Aurora Geospace Observation Network; Rcvr, receiver; SST, solid state telescope; UV, ultraviolet.
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From page 638... ...
ISP, Interstellar Probe; MCEM, Multipoint Comprehensive Eruptive Mission; HDTC, Heliospheric Dynamics Transient Constellation; EHC, Ecliptic Heliospheric Constellation; SPO, Solar Polar Orbiter; (Ionosphere, Thermosphere, Mesosphere) I-Circuit, Interhemispheric Circuit; BRAVO, Buoyancy Restoring-Force Atmospheric-Wave VerticalPropagation Observatory; Resolve; (Magnetosphere)
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From page 639... ...
NOTE: BRAVO, Buoyancy Restoring-Force Atmospheric-Wave Vertical-Propagation Observatory; COMPASS, Comprehensive Observations of Magnetospheric Particle Acceleration, Sources, and Sinks; EHC, Ecliptic Heliospheric Constellation; FY24, fiscal year 2024; HDTC, Heliospheric Dynamics Transient Constellation; I-Circuit, Interhemispheric Circuit; LAITIR, Low-Altitude Ionosphere and Thermosphere In Situ Researcher; Links, links between regions and scales in geospace; LV, launch vehicle; MCEM, Multipoint Comprehensive Eruptive Mission; OHMIC, Observatory for Heteroscale Magnetosphere-Ionosphere Coupling; SOURCE, Synchronized Observations of Upflow, Redistribution, Circulation, and Energization; SPO, Solar Polar Orbiter.
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From page 640... ...
• Long-term performance and lifetime of N G RTG power system • Uncertainties in mission-specific instrument modifications and updates • Launch: SL S B lock 2 w i t h Ce nt aur + ST A R 48 B V, nominal launch year: 2036 • Uncertainties in long range, long-term operations • Mission Design: H e li oce nt r i c e s cap e traj ectory, C3 = 304 km2/s2 with Jupiter G ravity Assist (J G A ) FIGURE G-6 Mission overview for Interstellar Probe mission concept.
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From page 641... ...
Spectroscopic • Adaptation of G amma-ray Spectroscopic Imager from B alloon Experiment to Space Mission Imager, Lyman-alpha H anle Coronagraph – Flight System: 7 .5 year lifetime, O ptical and X -B and communications, 3-axis stabilized, 1157 W deployed solar array and 4 0 Ah Li Ion battery, bipropellant propulsion system • Design Definition and Technical Maturation of the Lyman-alpha H anle Coronagraph • L1' – Payload (1 instrument) : Full Gamma-ray Spectroscopic Imager • H ard X -ray Instrument Resolution Improvement Over State of the Art – Flight System: 7 .5 year lifetime, O ptical and X -B and communications, 3-axis stabilized, 1157 W deployed solar array and 4 0 Ah Li Ion battery, bipropellant propulsion system • Solar Exclusion Z one for H igh Rate Laser Communications at L1 • L4 – Payload (1 instrument)
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From page 642... ...
, Faraday Cup • Development of spacecraft solar array for 0.4 AU operation – Flight System: 3-5-year life spacecraft, X -band communications, hydrazine propulsion system, 3 axis stabilized, powered by 2 x 2 m2 solar array wings and 24 Ah Li Ion battery, sun shield for thermal protection • Autonomous fault protection for safe recovery of spacecraft • Launch: V ulcan V C2S, nominal launch year: 2031 • Low launch mass margin depending on vehicle and launch opportunity • Mission Design: B allistic traj ectory to V enus with V G A to establish dispersed in 0.4 to 0.9 AU heliocentric orbits, C3 = 5.7 - 6.8 km2/s2 FIGURE G-8 Mission overview for the Heliospheric Dynamics Transient Constellation (HDTC) mission concept.
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From page 643... ...
– Flight System: 10 year lifetime, X -B and and K a-B and communications, 3-axis stabilized, deployed solar array and 36 Ah Li Ion battery, N2H 4 /N2O 4 biprop • Launch: Ecliptic: Falcon 9 launch with C3 = -1.7 km2/s2, G EO: Falcon 9 to G TO at 28.5 deg inc • Mission Design/Constellation: Ecliptic A: Leading Earth by + 120 deg, Ecliptic B : Trailing Earth by -120 deg, G EO: 35,7 86 km at 28.5 deg inclination FIGURE G-9 Mission overview for Ecliptic Heliospheric Constellation (EHC) mission concept.
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From page 644... ...
solar array wings and 7 0 Ah Li Ion battery • V erification of system magnetic noise identification for boomless magnetometer • Launch: V ulcan V C6S + STAR 27 H , nominal launch year: 2030 • Limitations of available solar power at Jupiter for critical flyby operations • Mission Design: H eliocentric escape traj ectory, C3 = 104 km2/s2 with Jupiter G ravity Assist (JG A) , and repeated V enus G ravity Assists (V G As)
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From page 645... ...
– Flight System: 30-month lifetime, S-B and & K a-B and communications, 3-axis stabilized,3.5 m2 • LEO satellite power limitations imposed by spacecraft volume and payload configuration solar array and 11 Ah Li Ion battery, prop for orbit phasing and maintenance • H EO Orbiters (2 satellites) • Timely deployment of constellation in unique orbit configuration – Payload (2 instruments)
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From page 646... ...
– Flight System: 2.5 year lifetime, S-B and communications (additional X -B and transmitter for M2/M3) , 3-axis stabilized,8 00 W deployed solar array and 30 Ah Li Ion battery, hydrazine monoprop • Launch: V ulcan V C0S to 500 km x 1200 km, 50 deg inclination drift orbit.
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From page 647... ...
for spacecraft bus • Capacity for production of 7 2 TLS instruments and 6U CubeSats • Launch: Electron launch vehicle with Photon kick stage and Terran/Tyvak N anosatellite • Fitting system within launch vehicle mass and volume constraints Launch Adapter System (N LAS) dispensers, nominal launch year: 2030 – 6 launches with 12 satellites per launch vehicle • Timely constellation deployment for 7 2 satellites in 12 orbit planes with no on-board satellite propulsion • Mission Design/Constellation: 500 – 7 00 km orbit at > 7 4 deg inclination, 6 satellites per plane, 12 planes total FIGURE G-13 Mission overview for Resolve mission concept.
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From page 648... ...
, and Education/P ublic O utreach Camera • Low Power Margin at End of Mission (EP O C) – Flight System: 7 .5-year life spacecraft, X -band communications, hydrazine propulsion system, • Impact of Radiation Environment at Jupiter radiation shielded avionics and instrumentation, spin stabilized, powered by 7 2 m2 roll out solar array wings and 4 2 Ah Li Ion battery • Low Allowances for System Mass G rowth • Launch: Falcon H eavy Expendable, nominal launch year: 2030 • Mission Design: DV -EG A traj ectory to Jupiter, C3 = 52 km2/s2 with two orbital phases at Jupiter (200 Rj x 5 Rj with 45 deg inclination and 45 Rj x 1.02 Rj at 15 deg inclination)
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From page 649... ...
– Payload: H O P E, SP B System, Fields Suite – Flight System (Spinner, M 4 ) : 2 year life spacecraft, X B and comm up to 7 1 kbps, LMP -103S propellant, P owerP C avionics, spinning star tracker, body-mounted solar panels – Launch: Falcon 9 or V ulcan R ideshare to GT O – O rbit: Geosynchronous T ransfer O rbit SOURCE = Synchroniz ed Observations of Upflow, Redistribution, Circulation, and Energiz ation FIGURE G-15 Mission overview for the Synchronized Observations of Upflow, Redistribution, Circulation, and Energization (SOURCE)
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From page 650... ...
– Flight System: 39-month life spacecraft, S-band communications up to 4 .5 Mbps, H ydrazine propellant system, smallsat avionics, 3-axis stabilized, powered by deployed solar panels PARAG ON = Plasma Acceleration, Reconfiguration, and Aurora G eospace Observation N etwork • Launch: Falcon 9, nominal launch: 2031 MagCon = Magnetospheric Constellation • Orbit: 9 Re circular at 7 0-9 0 deg inclination FIGURE G-16 Mission overview for Links mission concept. SOURCE: Created by The Aerospace Corporation.
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From page 651... ...
: U V O ptical Imager (U VI) – Flight System: 27 -month lifetime small satellite, S-B and and X -B and communications, 3-axis stabilized, 1.5 m2 solar array and 15 Ah Li Ion battery, hydrazine monoprop for orbit adj ustment • Launch: Falcon 9 from V andenberg AFB : Dispense Mother, Daughter, and Imaging Low at 500 x 5,500 km at 9 0 deg inclination, with each satellite using on-board propulsion to reach final orbit; use F9 upper stage to boost apogee to 43,800 km and dispense Imaging H igh • Mission Design/Constellation: Mother: 500 x 6000 km, Daughter: 1000 x 5500 km, Imaging Low: 500 x 6000 km, Imaging H igh: 500 x 43,800 km, all at 9 0 deg inclination FIGURE G-17 Mission overview for the Observatory for Heteroscale Magnetosphere-Ionosphere Coupling (OHMIC)
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From page 652... ...
, Electron Spectrometer (ES) • Impact of low altitude environment on instrument and spacecraft design – Flight System: 3-year life spacecraft, S-band communications, hydrazine propulsion system, 3 axis stabilized, powered body mounted 9.5 m2 cylindrical solar array and 26 Ah Li Ion battery • Future availability of launch vehicle suited to this mission • Launch: Minotaur-C (evolved Taurus)
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From page 653... ...
2023b. Thriving in Space: Ensuring the Future of Biological and Physical Sciences Research: A Decadal Survey for 2023–2032.
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