The Demonstrations & Science Experiment (DSX)
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1 The Demonstrations & Science Experiment (DSX) Radiation Belt Storm Probes Science Working Group 31 Aug 2010 Gregory Ginet, MIT/LL Michael Starks, AFRL Bob Johnston, AFRL Jay Albert, AFRL
2 The Team Program Office Systems Engineering Integration and Test Launch Segment Spacecraft Bus VLF Wave-Particle Interaction Experiment Space Environmental Effects Space Weather Experiments PROPULSION DIRECTORATE
3 Outline Introduction DSX experimental payloads Science question where is the 20 db? Science question how efficient are antennas in a plasma? Engineering requirement mapping MEO Summary
4 Mission Objectives Equatorial pitch-angle Three science experiments: 1) Wave-particle interactions (WPIx) Determine efficiency of injecting VLF into space plasmas in situ Determine global distribution of natural & man-made ELF-VLF waves Characterize and quantify wave-particle interactions 2) Space weather (SWx) Map MEO radiation & plasma environment Diagnose in-situ environment for wave generation experiments 3) Space environment effects (SFx) Quantify effects of MEO environment on new technologies Determine physical mechanisms responsible for material breakdown 6000 x km, 120, launch ~ Oct 2012 L* Magnetic phase space
5 Experimental Apparatus 8 m Z-Axis Booms VLF E-field Rx AC Magnetometer Tri-axial search coils Wave-Particle Interactions (WPIx) VLF transmitter & receivers Loss cone imager Vector magnetometer Space Weather (SWx) 5 particle & plasma detectors Space Environmental Effects (SFx) NASA Space Environment Testbed AFRL effects experiment Loss Cone Imager - High Sensitivity Telescope - Fixed Sensor Head Y-Axis Booms VLF E-field Tx/Rx VLF Transmitter & Receivers - Broadband receiver - Transmitter & tuning unit 8 m DC Vector Magnetometer ESPA Ring Interfaces between EELV & satellite Boom deployment test DSX satellite DSX being integrated!
6 Wave-Particle Interactions Payload Receiver (Stanford, Lockheed-Martin, NASA/Goddard): Three search coil magnetometers (3 B components) Two dipole antennas (2 E components) Frequency range: khz Sensitivity 1.0e-16 V 2 /m 2 /Hz (E) & 1.0e-11 nt 2 /Hz (B) Transmitter (UMass Lowell, SWRI, Lockheed-Martin): 3 50 khz at up to 500 kv (900 kv at end of life) khz at 1W (local electron density) Loss Cone Imager (Boston University, AFRL) High Sensitivity Telescope (HST): measures kev e- with 0.1 cm 2 -str geometric factor within 6.5 deg of loss cone Fixed Sensor Heads (FSH): 130 deg x 10 deg of pitch angle distribution for kev electrons every 167 msec Vector Magnetometer (UCLA, UMich) 0 8 Hz three-axis measurement at 0.1 nt accuracy Transmitter control & tuning units Broadband receiver & tri-axial search coils NASA GSFC 14 May 2007 Loss Cone Imager HST & FSH Vector magnetometer
7 Space Weather Payload Plasmasphere Ring current & aurora Radiation belts Protons LEESA LIPS HIPS HEPS HEPS Electrons LCI-FSH LIPS CEASE HIPS CEASE HIPS LEESA HEPS Energy (MeV) Energy (MeV) CEASE - Compact Environment Anomaly Sensor (Amptek, AFRL) LEESA - Low Energy Electrostatic Analyzer (AFRL) LIPS - Low Energy Imaging Particle Spectrometer (PSI) HIPS - High Energy Imaging Particle Spectrometer (PSI) HEPS - High Energy Particle Sensor (Amptek, ATC) Comprehensive SWx sensor suite will map full range of MEO space particle hazards LIPS CEASE LEESA
8 Space Weather Effects Payload CREDANCE Photometers SET Carrier (NASA-GSFC) NASA Space Environment Testbed (SET) Correlative Environment Monitor (QinetiQ) Dosimeter & deep-dielectric charging package DIME (Clemson Univ) Dosimetry Intercomparison and Miniaturization ELDRS (Arizona State) Development of space-based test platform for the characterization of proton effects and Enhanced Low Dose Rate Sensitivity (ELDRS) in bipolar junction transistors COTS-2 (CNES and NASA) Validation of single event effects mitigation via fault tolerant methodology Radiometers 1 AFRL/PRS COTS sensors Objective: directly measure changes in Optical transmission, Thermal absorption Thermal emission due to MEO radiation environment SFx experiments will quantify MEO environment effects on advanced spacecraft technologies & determine basic physics of breakdown
9 Science Question Ground-based VLF Injection NPM VLF transmitter Sequence of standard models used to estimate VLF distribution in space Power flux on the ground (LFCOM) Power flux at 1000 km (LFCOM + Helliwell) Power flux in the magnetosphere (LFCOM + Helliwell + PowerTrace)
10 Science Question Where is the 20 db? Abel & Thorne (1998) Starks, et al. (2008) Ground transmitter VLF needed in the inner magnetosphere but where is it? If not ground transmitters then what? Could lightning be more effective then previously thought?
11 Science Question It s not the Absorption Model The four models operate entirely differently: empirical, mode theory, finite differences, full wave All predict essentially the same ionospheric penetration fields However, all of them overestimate the fields by 20 db or more. Questions: Where is the transmitter power going? Non-linear lower-hyrbid wave density fluctuation scattering? What is scattering the particles at L < 2? Could lightning be more effective then previously thought?
12 RBSP Magnetic Field Line Footprints 1 week (typical) Jul Dec Lightning Flash Rates
13 n (#/cm^3) B (Gauss) DSX Plasma Environment Magnetic field DSX transmitter Plasma density Radius (Re) Characteristic frequencies
14 Cold Plasma Regime m i /m e L R X O L R X R X S=0 L=0 R Vacuum limit R L O X
15 Science Question What is the Radiation Efficiency? More complex than in vacuum I plasma I 1 I V = V 2 -V 1 d I I I dt Far-field power radiated ~ 1 2 plasma Antenna fields heat local plasma Anisotropic medium dictates complex power flow
16 Spiral Modeling Approach Vacuum dipole radiation in vacuo out to 10 km then cold plasma propagation Linear cold plasma voltage and current distribution specified on antenna immersed in a cold plasma Self-consistent linear cold plasma voltage on terminals specified, current distribution calculated selfconsistently for antenna immersed in a cold plasma Sheath & plasma heating effects included
17 Global Power Distribution 3 khz Satellite at 6000 km altitude, 0 magnetic lat, vacuum antenna limit; 3 khz EQUATORIAL PLANE MERIDIONAL PLANE L=4 L=3 3 khz 6000 km L=2 L=3 L=4 Critical Unknown: Importance of scattering and mode-conversion on power and k-spectrum
18 Global Power Distribution 10 khz Satellite at 6000 km altitude, 0 magnetic lat, vacuum antenna limit; 10 khz EQUATORIAL PLANE MERIDIONAL PLANE L=4 L=3 L=2 L=3 L=4 Magnetospheric reflection destines rays for lower altitudes at 10 khz as compared to 3 khz
19 Global Power Distribution Off Equator Satellite at 6000 km altitude, 30 magnetic lat, vacuum antenna limit; 10 khz EQUATORIAL PLANE MERIDIONAL PLANE L=4 L=3 L=2 L=3 L=4 The off-equatorial transmitters lead to very complex field distributions.
20 RBSP Magnetic Conjunctions Same field line Same drift shell & pitch angle
21 RBSP Physical Conjunctions Same point Closest approach ~ 422 km
22 Why Map the MEO Environment? SCATHA Surface ESD CRRES MEP-SEU Anomalies CRRES VTCW Anomalies Satellite designers need a definitive model of the trapped energetic particle and plasma environment to include: Quantitative accuracy Indications of uncertainty Flux probability of occurrence and worst cases for different exposure periods Broad energy ranges Complete spatial coverage MEO is sorely under sampled! Slot HEO SEUs (Dose behind 82.5 mils Al) GPS GEO TSX5 HEO Internal Charging RBSP Outer Belt LEO DSX ICO Inner Belt GEO Surface Charging SCATHA Slot L ~ Equatorial Radial Distance (R E )
23 kev Energy (kev) kev L shell (Re) kev New 10 Standard 3 10 Radiation Belt Model AP9/AE Satellite data Statistical & physics based analysis Mission orbit TEM1c PC-3 (9.36%) TEM1c PC-3 (9.36%) TEM1c PC-4 (6.77%) TEM1c 18 PC-4 months (6.77%) 10 + = Flux maps L eq =90 o L Statistical Monte-Carlo Model log 10 Flux (#/cm 2 eq =90 o User application New AP-9/AE-9 model being developed by NRO - AFRL - Aerospace MIT/LL - LANL consortium Provides significant improvement in spectral coverage, error estimation and statistical output Needed by satellite engineers to control risk, maximize capability and reduce cost Version Beta released Apr 2010 and now being evaluated by 20+ independent spacecraft engineers from industry and government Version 1.0 due in June 2011 Version 2.0 (~2015) will utilize measurements from NASA Radiation Belt Storm Probes (RBSP) and AFRL DSX missions 23 UNCLASSIFIED
24 - RBSP Summary DSX is manifest for launch as secondary payload on DMSP F-19 with launch in Oct 2012 DSX will provide high latitude wave & particle coverage in the slot region to complement RBSP low latitude coverage Missing 20 db of VLF power is a big inner magnetosphere question Tremendous opportunities for bi-static VLF transmit-receive measurements Validate chorus hiss conversion model Determine VLF antenna transmission efficiency Lots of good science to be done
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