JUpiter Magnetos Pheric boundary Explore R JUMPER R

JUpiter Magnetos. Pheric boundary Explore. R (JUMPER) R. W. Ebert 1, F. Allegrini 1, F. Bagenal 2, C. Beebe 1, M. A. Dayeh 1, M. I. Desai 1, D. E George 1, J. Hanley 1, P. Mokashi 1, N. Murphy 3, P. W. Valek 1, D. Wenkert 3, A. Wolf 3, C. -W. L. Yen 3 1 Sw. RI, 2 CU/LASP, 3 NASA/JPL The Planetary Cube. Sats Symposium NASA GSFC, Thursday, August 16 th, 2018

Jupiter’s Magnetosphere Bagenal and Bartlett JUMPER focuses on two science topics: 1. The solar wind’s impact on Jupiter’s magnetosphere. 2. Mass and energy transport through Jupiter’s magnetosphere.

Science Questions Mission Overview Mission Design 1. How does the solar wind (SW) influence the configuration and dynamics of Jupiter’s magnetosphere? 1. How does the SW interact with Jupiter’s magnetopause? 1. What are the flux and energy spectra of energetic neutral atoms escaping from Jupiter’s magnetosphere? Flight System Key Performance Characteristics

Science Question #1 How does the solar wind (SW) influence the configuration and dynamics of Jupiter’s magnetosphere? JUMPER conducts simultaneous observations of Jupiter’s magnetosphere with the primary spacecraft and/or Earth-based observatories.

Science Question #2 How does the SW interact with Jupiter’s magnetopause? Delamere & Bagenal 2010 Ebert et al. 2017 Observations of magnetic reconnection and Kelvin-Helmholtz waves at Jupiter’s magnetopause are limited to non-existent.

Science Question #3 What are the flux and energy spectra of energetic neutral atoms (ENAs) escaping Jupiter’s magnetosphere? Mauk et al. 2004 Mitchell et al. 2004

Instrument Complement Instrument Ion and Electron Sensor (IES) Magnetometer (MAG) Neutral Atom Imager (NAI) Baseline Design Electrostatic Analyzer + Detector Vector Helium Magnetometer Single Pixel Imager Operating Range/Resolution 4. 3 e. V/q – 17. 6 ke. V/q ΔE/E: ~8% ± 1000 n. T <20 p. T/√Hz at 1 Hz ~0. 5 – 10 ke. V ΔE/E: ~50% Field-of-view 90° x 270° 3 -axis 6. 5° x 6. 5° Time Resolution 128 s 1 - 60 s 600 s Mass 2. 2 kg ~0. 74 kg 9. 4 kg Power 1. 85 W ~ 3. 6 W ~6 W Heritage Rosetta/IES INSPIRE, Cu. SP, Europa/ICEMAG TWINS, IBEX-Hi, IMAGE/ MENA, Cassini/INCA

Mission Design • JUMPER launches with primary spacecraft. • Primary spacecraft + JUMPER arrive at Jupiter. • JUMPER rides with primary spacecraft through Jupiter orbit insertion.

Flight System Key Functional Systems - Mechanical, Structural, and Thermal (MST). - Electrical Power System (EPS). - Hydrazine Propulsion System (HPS). - Flight Avionics System (FAS). - Communication and Data System (CDS). JUMPER utilizes, to the greatest extent possible, commercial off-the-shelf (COTS) systems & components.

Key Functional Systems Mechanical, Thermal, Structural - Radiation vault. - Support columns & body panels. - Clamp-band separation system. - Thermal accommodations. Electrical Power System - Battery backed 28 V bus (640 Whr). - Solar Arrays: 4 x triple deployed. - Peak-power tracker: 94% efficiency. - Low-voltage power supply (LVPS).

Key Functional Systems Hydrazine Propulsion System Flight Avionics

Primary Spacecraft Accommodation

Launch Vehicle Interface

JUMPER Summary § JUMPER is a Jupiter orbiting Small. Sat mission concept. § Science goal is to study (i) the solar wind’s impact on and (ii) mass and energy transport through Jupiter’s magnetosphere. § Project funded through NASA PSDS 3 program. § Final report delivered to NASA on 12/29/2017. § Paper published in IEEE 2018 Aerospace Conference Proceedings. § This mission concept is applicable to other planetary systems. § A mission proposal was submitted to SIMPLEX program that leveraged technical work developed for JUMPER (next slide).

§ SOAR is a Small. Sat mission to Mars with a targeted and compelling science investigation. § § Science goal: Characterize the large-scale interaction between the solar wind and Martian space environment. Solar wind-Mars interactions studied using in-situ and remote sensing observations. Mission design § 480 day interplanetary cruise + orbit transfer period. § 10 month science mission. The SOAR flight system meets the mass and volume requirements for an ESPA-class Small. Sat. § SOAR proposal submitted to SIMPLEX program for review.