IMESA-R Integrated Miniaturized Electrostatic Analyzer Reflight

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1 IMESA-R IMESA-R Integrated Miniaturized Electrostatic Analyzer Reflight Dr. Parris Neal Cadet First Class Alex Strom Cadet First Class Nikolas Taormina USAF Academy Principal Investigator: Geoff McHarg

imesa-r: A space weather constellation Four inexpensive space weather instruments Each instrument provides two measurements Low energy plasma (Electrostatic Analyzer) Radiation

5 W with dosimeter DoD Space Test Program (STP) providing flights on four different spacecraft Green Propellant Infusion Mission (GPIM) FY16 Orbital Test Bed (OTB) FY-16 STPSat-4

2 imesa-r: A space weather constellation Four inexpensive space weather instruments Each instrument provides two measurements Low energy plasma (Electrostatic Analyzer) Radiation (Dosimeter) Low size, weight, power (SWAP) 10x12x4.5 cm 2.1 W without dosimeter, 2.5 W with dosimeter DoD Space Test Program (STP) providing flights on four different spacecraft Green Propellant Infusion Mission (GPIM) FY16 Orbital Test Bed (OTB) FY-16 STPSat-4 FY-17 STPSat-5 TBD First DoD space weather constellation 24 degrees inclination km (GPIM and OTB) 51.6 degrees inclination 425 km (STPSat-4) 97 degrees inclination 550 km (STP Sat-5) imesa-r flight instrument for GPIM imesa-r Constellation with four concurrent satellites 2

Scientific and Military Problem Big Picture: Operators need to quickly distinguish between environmentally induced and possible hostile anomalies imesa-r concentrates on ionosphere and ionizing

effects, deep dielectric charging Forecasting is a priority requires nowcast Nowcast requires multipoint measurements imesa-r provides 4 satellite constellation Knipp, Understanding Space Weather,

3 Scientific and Military Problem Big Picture: Operators need to quickly distinguish between environmentally induced and possible hostile anomalies imesa-r concentrates on ionosphere and ionizing radiation Ionosphere: Plasma irregularities ( bubbles ) cause scintillation Loss of GPS lock <50% availability* during severe scintillation Loss of SATCOM Radiation: Single event upset, dose effects, deep dielectric charging Forecasting is a priority requires nowcast Nowcast requires multipoint measurements imesa-r provides 4 satellite constellation Knipp, Understanding Space Weather, 2011 * For LPV-200. Seo, J, PhD thesis, Stanford Univ, 2010 Van Allen Radiation belt image created using data from NASA Van Allen Probes: Note emergence of third transition belt: Image Credit APL, NASA 3

reflight Mature hardware, software, electronics Demonstrated success on three missions Future: GPIM Launch Mid-2016

4 Heritage and Future Technology patented by USAFA Development funded by AFOSR and AFRL IMESA launched on: MISSE7(ISS) imesa = 1 st data collect STP-H4 MESA launched Aug 2013 = 1 st reflight STPSat-3 imesa launch Nov 2013= 2 nd reflight Mature hardware, software, electronics Demonstrated success on three missions Future: GPIM Launch Mid-2016 OTB Launch Mid-2016 STP-Sat 4 Launch Read Aug 2017 STP-Sat 5 TBD MISSE7 Credit:NASA imesa STPSat-3 Credit Ball Aerospace 4

STPSat-3 IMESA-R Data Top panel: raw data product: energy-time spectrogram Density increases into sunlight Energy increases into sunlight 2nd panel down: Ion Temperature 3rd panel down: Ion Density

5 STPSat-3 IMESA-R Data Top panel: raw data product: energy-time spectrogram Density increases into sunlight Energy increases into sunlight 2nd panel down: Ion Temperature 3rd panel down: Ion Density Bottom panel: derived spacecraft charging Issues: Energy varying over daynight cycle between ev Data drop out over portion of orbit Temperatures not well resolved EMI due to power converters STPSat-3 Data: imesa data product for one orbit 17 Feb

Changes for imesa-r flights 3-6 New electrostatic analyzer (ESA) design Improved temperature measurements Reduces number of plates ease of manufacture Switchable range on ESA Allows for different

6 Changes for imesa-r flights 3-6 New electrostatic analyzer (ESA) design Improved temperature measurements Reduces number of plates ease of manufacture Switchable range on ESA Allows for different host S/C charging Programmable gain amplifier Assures data collection during entire orbit Higher transimpedance amplifier gain New power supply design Reduces EMI Change of one power supply allows flights on many different satellites Added dosimeter Allows ionizing radiation monitoring Rewrote software Assures modularity and future upgrades ions New ESA Design Single mezzanine bus: -6dB noise reduction Collection Anode 6

imesa-r Design Philosophy Multi-disciplinary Physics ESA design, calibration and analysis Physics Dosimeter modelling and calibration Electrical and

qualification Good enough versus gold standard measurements Numbers count in terms of improvement to model output Small SWAP minimizes host S/C impact

7 imesa-r Design Philosophy Multi-disciplinary Physics ESA design, calibration and analysis Physics Dosimeter modelling and calibration Electrical and Computer Engineering: Electronics design and test Use of Commercial Off The Shelf (COTS) components Reduced cost East of integration Requires space qualification Good enough versus gold standard measurements Numbers count in terms of improvement to model output Small SWAP minimizes host S/C impact and increases Evolutionary design changes Pick a basic technology Develop on-orbit flight heritage learn as you go Change when needed, not because you can 7

8 How many measurements are enough? Modelled three orbital scenarios (Balthazor et al. 2015, Radio Science) Compared ionospheric model output with and without imesa on orbit Collaborative effort with Utah State University A: 10x 500 km String of pearls 90º inclination 1 launch B: 10x 350 km String of pearls 90º inclination 1 launch C: 25/5/1 Walker 500 km 60º inclination 5 launches 5 satellites per launch ~1-10 year lifetime Example 25 satellite Walker Constellation 8

Scenario A,B ( string of pearls ) Vertical propagation of information GPS-TEC only GPS-TEC + Sats @ 500 km GPS-TEC + Sats @ 350 km (A) (B) Converges towards truth with 10

9 Scenario A,B ( string of pearls ) Vertical propagation of information GPS-TEC only GPS-TEC km GPS-TEC km (A) (B) Converges towards truth with 10 satellites Model improvements at all altitudes not just orbital altitude Knowledge moves along field lines Can quantify accepted error and use to fine-tune orbital parameters 9

10 Mean height of F2 peak improvement quantification Various metrics can be used to quantify improvement by adding IMESAs Metrics can depend on conditions position, time, geomagnetic activity 25 IMESAs improves RMS to ~10 km imesas improves Skill score to > 75% Without IMESA With IMESA RMS deviation of hmf2 (global sum) Skill score of hmf2 (global sum)

imesa-r Mechanical Overview Fits in a 45mm x 102mm x 126mm envelope (without RBF Cover)

6061-T651 per ASTM-B209 Printed circuit boards (PCBs) are enclosed within the assembly

(for future missions) Modular structure design to be barnacle mount or panel flush mount

11 imesa-r Mechanical Overview Fits in a 45mm x 102mm x 126mm envelope (without RBF Cover) Mass is NTE 1kg (including mounting hardware) Mounting interface is six #6-32 Bolts Al 6061-T651 per ASTM-B209 Printed circuit boards (PCBs) are enclosed within the assembly Designed to fit PC-104 boards Keying features on boards Easy integration into CubeSats (for future missions) Modular structure design to be barnacle mount or panel flush mount Easily accessible Programming ports in either configuration PC-104 Board Size (with Keying Features) 11

12 imesa-r Exploded View RBF Cover Enclosure Plate Lower Mounting Enclosure Brains Board Connector Ring Heads Board Assembly Upper Enclosure Programming Port Blanking Plate 12

13 Hardware Simplified Block Diagram = Switchable gain amplification chain = imesa-r peripherals = Data and command pathways =Signal paths 13

14 Software Block Diagram Simple heritage code design Rewritten from scratch for OTB & GPIM IMESA-Rs Minor changes anticipated to accommodate μcontroller change Command processing Sweep processing Spacecraft communication 14

space by doing a real mission end to end

space enterprise USAFA is developing the

15 imesa-r Summary Unique 4 satellite constellation for space weather Simplified design allows reduced cost, increased numbers of measurements Cadets learn about space by doing a real mission end to end Multi-disciplinary USAFA effort emulates AF space enterprise USAFA is developing the next generation of Space Professionals GPIM OTB STP-Sat4 STP-Sat5 15

9 Aug 04 Getting Technology to Space for the Warfighter

9 Aug 04 Getting Technology to Space for the Warfighter 1 SMC Detachment 12 - The Dirty Dozen Space Test Program-1 (STP-1) First of its Kind! Major Ray Galik STP-1 Program Manager 9 Aug 2004 Overview STP-1 Mission summary STP-1 Firsts Manifest Changes Space