Magnetospheric MultiScale Mission (MMS) Overview

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Presentation transcript:

Magnetospheric MultiScale Mission (MMS) Overview Conrad Schiff

MMS Launch The MMS mission was launched on March 13, 2015 aboard an Atlas V rocket from Space Launch Complex 40, Cape Canaveral, Florida Each of the four observatories were successfully released at five minute intervals spinning at 3 rpm approximately 1.5 hours after launch

Science Goals Study magnetic reconnection in the Earth's magnetosphere Magnetic reconnection converts magnetic energy into kinetic energy Oppositely directed parallel field lines are pinched They join and snap apart like a breaking rubber band Benefit: understanding of how the Earth lives with the Sun (e.g. Class X Flash 0156 GMT Tuesday, Feb. 15, 2011)‏ Power grid problems Communications disruption Aurora formation Credit: European Space Agency

Flight Dynamics Concept Use the formation as a ‘science instrument’ to study the magnetosphere Night-side science (neutral sheet) bound by power (limits shadow duration) Shadow Need to prevent close approaches 30-400 km Magnetic Field Lines Maneuvers used to maintain formation against relative drift (DV) and to maintain attitude pointing (DH) 10-160 km Sun Formation scale matches science scale

MMS Flight Summary (March 12, 2014 10:34 pm EST) GSE Time Multiple opportunities for joint observations with THEMIS and Van Allen Probes

MMS Instrument Suite Components (view looking from the bottom of the IS Deck) DES DIS * On S/C Deck ADP - Axial Double Probe AFG - Analog Flux Gate Magnetometer (mounted on boom) ASPOC - Active Spacecraft Potential Control CEB - Central Electronics Box (Fields) CIDP - Central Instrument Data Processor DES - Dual Electron Spectrometer DFG - Digital Flux Gate Magnetometer (mounted on boom) DIS - Dual Ion Spectrometer EDI/GDU - Electron Drift Instrument/ Gun Detector Unit EIS - Energetic Ion Spectrometer FEEPS - Fly’s Eye Energetic Particle Sensors HPCA - Hot Plasma Composition Analyzer IDPU - Instrument Data Processing Unit (FPI) SCM - Search-Coil Magnetometer (mounted on boom) SDP - Spin-Plane Double Probe TP/HPDB – Test Panel Heater Power Distribution Box SCM Pre-Amp* EDI-GDU SDP FEEPS* HPCA EIS AEB ASPOC SDP ADP (2x) CEB DIS DES DES DIS ASPOC SDP Purge Man FEEPS EDI-GDU CIDP SDP Safe/Arm Panel TP/HPDB DIS DES

Spacecraft Fully Deployed Spin axis – within 2.5 deg of ecliptic north Spin rate – 3 +/- 0.2 rpm Boom Lengths Mag boom: 5 m Axial boom: ≈ 12.5 m Wire boom 60 m Spacecraft Dimensions Diameter: ≈ 3.4 m Height: ≈ 1.2 m Onboard controller tasked with performing all spin-attitude and delta-V maneuvers Not to scale

Spacecraft GN&C Block Diagram Sensors Actuator ACS Flight SW Resides in C&DH DSS Data process Sun Acq DSS Sun Pulse Sun elevation angle Delta-H Command Generation (Create arm table) Star Sensors Data process C&DH Processor Card pps Thruster CMD Star Sensors Delta-V (w or w/o attitude/ rate control) EVD All needed Thrusters Quaternion Body rate AMS data process Delta-Vi 10 s averaged acceleration Table, pps CMD verified AMS Delta-V Acceleration Checkout Science Thrust Tlm ACS sensor Data 20 MHz frequency signal 10 s averaged acceleration; thruster firing status Orbit maneuver cmd Inertia ratio Attitude/rate cmd Navigator (GEONS) USO FD Ground Support System (FDGSS): GEONS monitoring Orbit maneuver planning, monitoring and calibration Orbit product generation Attitude Ground System (AGS): AMS parameter estimation Attitude maneuver planning Nav. Data via C&DH 8