Assessment of the payload for - PowerPoint Presentation

Slide1

Assessment of the payload for

space

weather monitoring missions situated at the L1 & L5 Lagrangian points

Yulia Bogdanova

1, Jackie Davies1, Richard Harrison1, Mario Bisi1, Mike Hapgood1, Mark Gibbs2, David Jackson2, Oliver Turnbull3, David Riley3, Reuben Wright3, Alessandro Grasso4, Marc Scheper4

RAL Space, STFC, UK; (2)

Met Office,

UK;

(3) Deimos

Space UK

Ltd, UK; (4) OHB

System

AG,

GermanySlide2

Talk Outline

Motivation

L1 & L5 mission objectives Recommended payload and its performanceSlide3

Motivation/justificationProvision

of services to the users and customersSatellite designers / builders Satellite operators Human

spaceflightLaunch providers / operationsTrans‐ionospheric radio communications, satellite navigation, data relaySpace Surveillance and Tracking ServicesGeneral Data Services

Non‐space systems operators• Aviation• Power grid operators• Oil drilling/exploration• Road transport• Tourism

Services include: forecasting, activity warnings, nowcasting, post-event analysis and archives.The mission payload assessment was based on the analysis of the ESA SSA Customer Requirements, System Requirements and Product Specification Documents . Slide4

L1 and L5 Missions

L1

In-situ observations & solar monitoring for space weather forecasting

L5

Remote sensing & in-situ observations to improve SWE forecasting capabilities

Observational requirements for each mission was assessed as for stand-alone mission.

Synergies between two missions also have been considered.Slide5

L1 mission objectivesPrimaryGeomagnetic storm

forecasting with lead times of up to 12 hours (sufficient to forecast the arrival of a very fast Coronal Mass Ejections (CMEs) with ≤ 18 hour transit time) -> decide on mitigation actionsIdentification of the launch of Earth directed CMEs, and their motion away

from the Sun, including the prediction of arrival times at EarthProvision of improved inputs to heliospheric models, including estimates of the background solar wind and CME parametrisation, to improve CME arrival time and solar wind predictions at EarthMeasurement of vector components of the Interplanetary Magnetic Field (IMF)Measurement of speed, density and temperature of solar wind

Monitoring of low energy ion precursors of CME shock arrival at EarthMonitoring of solar energetic particles impacting the terrestrial systemEnable real‐time assessment of Earth‐directed CMEs

SecondaryMonitoring of developing solar activity with potential Earth impactProvision of stable, continuous space weather data (model development andunderpinning space weather research)Slide6

L5 mission objectivesPrimaryGeomagnetic storm forecasting with lead times of up to 12 hours

(as for L1)Improvement of assessment of CME motion and density, in the corona and heliosphere, using a different observational perspective to the L1 observationsProvision of improved inputs to heliospheric models to improve CME arrival time and

solar wind predictions at EarthMeasurement of vector components of the IMF and the speed, density and temperature in solar wind features (e.g., SIRs) rotating towards Earth.Monitoring of active regions development up to 4‐5 days beyond the East limb identify developing solar activities with potential for Earth‐impactEnable real‐time assessment of Earth‐directed CMEs

SecondaryMonitoring of low energy ion signatures at L5 as indicate an Earth‐directed CME shockProvision of stable, continuous space weather data (model development

and underpinning space weather research)Enhancing: ‘To provide a broader view of solar energetic particle events occurring in the inner solar system’Slide7

PSD

Ref

Measurement

L1

L5

L1-008-M

Interplanetary Magnetic

Field

C

C

L1-009-M

Solar

Wind Bulk

Velocity

C

C

L1-010-M

Solar

Wind Bulk

Density

C

C

L1-011-M

Solar

Wind Temperature CCL1-001-M >10 MeV solar wind protonsCEL1-005-M30 keV/nuc -1 MeV/nuc solar wind ionsCEL1-003-M1-10 MeV solar wind protons ON/RL1-007-M30 keV – 8 MeV solar wind electronsOESU-005-MPhotospheric Solar-Disk Magnetic-FieldCCSU-017-MPhotospheric Solar-Disk White-light ImagesCCSU-015-M, SU-021-M EUV Images of the SunOOSU-025-M, SU-022-M White-light wide-angle Coronagraph ImagesCCSU-032-MHeliospheric ImagesOCSU-027-MSolar X-ray fluxOOSU-026-MSolar Radio spectrographic ObservationsEEL1-006-M2-50 MeV solar wind electronsEN/RL1-004-M1-10 MeV/nuc solar wind ionsEN/RL1-002-M> 10 MeV/nuc solar wind ionsEN/R

Observational requirementsSlide8

SWE instruments – general requirementsThe instruments should be optimised for the s

pace weather monitoring: Robust, radiation tolerant, continuous operation 24/7Based on proven design and techniquesEasy to operate and calibrateF

ast downlink for nowcastingShould measure extreme behaviour accuratelyLimitations on the telemetry, mass & power budget.Assessment

of the instruments requirements for two levels:Threshold - satisfies the basic need of the customer and is required to maintain current capability of the services.Goal - provides substantial improvements in the Space Weather services capability.

Steenburgh et al., 2014Slide9

MagnetographMandatory

: L1 and L5 Justification:To provide basis data on which to model the background solar wind (including SIRs/CIRs) for arrival time prediction of CMEs

at Earth. To inspect the magnetic field in order to provide advanced warning of developing activity.To monitor white-light Sun to provide

an indicator of sunspot activity, and their potential complexity and development.

Performance requirements:FoV: 42.6 x 42.6 arcmin centred on Sun centre

Spatial

resolution

: 5

arcsec

(T), 2

arcsec

(G

)

Dynamic

range: ± 4

kG

,

12 bits

Accuracy: 10

-3

of continuum intensity

T

: the line of sight

magnetograph; G

: vector

magn

.

Pointing stability: 0.5/0.2 arcsec over 30 s (T, G)Cadence: 30 min (T), 10 min (G) Latency: 60 min (T),10/30 min (L1/L5 G)Heritage/baseline: PHI instrument on Solar OrbiterSlide10

EUV ImagerMandatory:

L1 and L5Justification:To monitor the chromosphere/corona for impending Earth-affecting solar activity (occurrence of prominence eruption, situation of coronal holes, etc.), particularly on the region of the Sun that is yet to rotate to the longitude of Earth.

Performance requirements:

T: Full disk image in Fe XII 193 A lineG: Full disk image in Fe XII 193 A, He II 304 A, Fe IX 171 A and Fe XIV 211 A

FoV: 42.6 x 42.6 arcmin image centred on Sun centre Spatial resolution: 5 arcsec (T), 2 arcsec (G)Dynamic range: 14 bits Pointing stability: 0.5/0.2 arcsec (T/G) over 5 s

Cadence

: 5/20 min ( L1/L5 T), 5/10 min (L1/L5 G)

Latency: 10/60 min (L1/L5 T), 10/30 min (L1/L5 G)

Heritage/baseline:

SOHO/EIT

, SDO/AIA,

STEREO/EUVI, ESIO

(EUV Solar Imager for Operations

)Slide11

CoronagraphMandatory:

L1 and L5Justification:To enable definitive, early and critical identification of Earth-directed CMEs and to enable forecasting, with the longest possible lead time, of their arrival at Earth.

To provide the basis of the characterisation of CMEs for inclusion into the majority of current operational modelling endeavours to predict their Earth arrival. Performance requirements:FoV: 3-22

Rs (T); 2.5-30 Rs (G)Spatial resolution: 2 arcmin

Dynamic range: 16 bitsSensitivuty: detection of signal to 2 x 10-13 Bo Accuracy: 20% of CME signal; SNR > 2 (T), SNR > 4 (G)Cadence: 10 min (T); 5 min (G)

Latency: 15/25 min (L1/L5 T), 5/15 min (L1/L5 G)

Heritage/baseline:

LASCO C2 & C3 and COR, SCOPE

(Solar Coronagraph for

OPErations

)

instrument

.Slide12

Heliospheric ImagerMandatory: L1

and L5Justification:To

enable tracking of Earth-directed CMEs over much of their propagation path, in order to mitigate deficiencies in arrival times predictions based on the use alone of near-Sun data. To provide information on the background solar wind.

Heritage/baseline:

HI on STEREOPerformance requirements:FoV: 10-40 deg (L1, T), 4-60 deg (L1 G, L5) elongation coverage from Sun-centre along ecliptic.

Two

cameras

required for higher FoV

Two instruments

(

L1

)

,

one instrument (

L5)

Spatial resolution:

< 4

arcmin

Dynamic range: 24 bits

Sensitivity

:

detection of intensity down to ~ 10

-14

Bo (T), 3x 10

-15

Bo (G

)

Accuracy: 20% of CME signalCadence: 60 min (T), 30 min (G)Latency: 20/25 min (L1/L5 T), 10/15 min (L1/L5 G)Slide13

X-ray sensorMandatory:

L1 and L5Justification:To monitor flare activity in integrated 1-8 Angstrom band. This measurement provides important information in order to predict HF radio wave absorption in the upper atmosphere D-region.

Performance requirements:

Intergrated solar X-ray fluxRange: 1-8 Å (T), 0.5-8 Å (G)Dynamic range: to cover events in

range 2x10-8 – 2x10-3 W/m2Accuracy: 15% Cadence: 1 min Latency: 10/20 min (L1/L5 T); 5/15 min (L1/L5 G)

Heritage/baseline

: SMART-1

XSM,

BepiColombo

SIXSSlide14

Radio-burst SpectrometerEnhancing: L1 and L5

Justification:To track shocks in the inner heliosphere (Type II). Observations from the one location can confirm what type of radio bursts is observed, e.g., Type II or Type IV.

To identify a shock, its distance from the Sun and speed, these data in combination with other data sets can be used for definition of the CME direction.

Performance requirements:

Frequency range: 40 kHz - 10 MHz (T); 10 kHz-60 MHz (G)Dynamic range depends on the frequency range, 50 -120/110 dB Cadence: 30 s (T); For G: < 150 kHz - 10 s; > 150 kHz - 1 s; > 30 MHz - 0.1sLatency: 40 min (T), 10/15 min (L1/L2 G)

Heritage/baseline:

STEREO

S/WAVES instrument. Slide15

MagnetometerMandatory:

L1 and L5Justification:To provide a short lead-time forecast and nowcast.

To define the geoeffectiveness of the CMEs (on L1) and SIRs (on L1 and L5). To provide data for the magnetospheric dynamics forecast models.

Performance requirements:

IMF vector with 3-componentsRange: 0.1 – 200 nT for every componentAccuracy: ± 1nT (T); ± 0.5 nT (G)

Cadence

: 1 min (T); 1 sec ( G ) 

Latency:

5/20

min

(L1/L5 T

);

1/15

min

(L1/L5 G

)

2

sensors: one

in-board

and other

out-board.

Heritage/baseline:

BepiColombo

, Juice, Rosetta, VEX,

Cluster, MAG

on Solar

Orbiter,

triaxial

fluxgate magnetometerSlide16

Solar Wind Analyser

Mandatory

: L1 and L5Justification:To provide measurements of the solar wind density, velocity and temperature. crucial in prediction and analysis of the impacts of the geomagnetic storms on the magnetosphere, ionosphere and atmosphere.

To provide a short lead-time forecast of the arrival of the CMRs and SIRs at Earth.To provide data for the magnetospheric dynamics forecast models.

Byrne

et al, 2010

Performance requirements

:

Velocity:

Range: 200-2500 km/s (T); 100-3000 km/s (G)

5% relative

accuracy

Density:

Range: 0.1 – 150 cm

-3

(T); 0.1-200 cm

-3

(G)

5% absolute

accuracy

Temperature

Range: 40,000-1,000,000 K (T); 10,000 – 2,000,000 (G)

5% absolute accuracy Slide17

Solar Wind Analyser

Performance requirements:Top-hat electrostatic analyser with segmented anode combined with aperture deflection plates.

Instrument should produce 3D phase space density data and produce on-board moments (velocity, density and temperature).FoV: 45⁰ (azimuthal) x ±

22.5⁰ (elevation)Angular resolution: 5⁰ x5⁰,

9 azimuthal bins and 9 polar binsNumber of energy bins: 30 binsEnergy range: 70 eV/q – 32.6 keV/q (T), ~ 50 eV/q – 47 keV/q (G)∆E/E =~10% Dynamic range: 104 - 2x1010 #/(cm2-

sec-sr)

Cadence

: 1 min (T); 1 sec (G)

Latency: 5/20 min (L1/L5 T); 1/15 min (L1/L5 G)

Heritage/baseline:

HIA-CIS on Cluster, SWA-PAS and SWA-EAS on Solar OrbiterSlide18

Energetic particle instruments

Justification:

To

p

rovide early warning on the CME shock propagation.To monitor radiation storms and its effects, including disruption and damage of the sensitive exposed to space systems such as solar panels and sensors. e.g., through single event effects, radiation damage and dielectric discharge.To monitor high-energy components of the radiation storms which can affect aircraft (if > 150 MeV) and ground systems (if > 500 MeV).Slide19

In-situ payload

ClassificationInstrumentObservationsInstrument requirements

HeritageL1: Mandatory L5: EnhancingLow energy ion detector30 keV/nuc- 1 MeV/nuc ions

Ions:p+, alpha, CNO groups and Fe

p+, alpha, CNO groups, Si/Ne, Fe, Ni and single measurement for heavy ions FoV: 60deg half-width1 (2) sensors, along and opposite to Parker spiralLimited dynamic range targeting SEP fluxesAccuracy: ±15% relative accuracy, ±50% (±40%)

absolute accuracy

4

(5)

energy bins

SIT on STEREO

L1: Enhancing

Medium

energy ion detector

1-10 MeV/nuc ions

5

(10)

energy

bins

LET

on STEREO

L1: Enhancing

High energy ion detector

> 10 MeV/nuc

ions

Range: 10 -500

(1000)

MeV/nuc

5

(10)

energy binsHET on STEREOL1: Mandatory Medium energy proton detector1-10 MeV protons3 (5) energy binsSEPT and LET on STEREO, NGRM L1: MandatoryL5: EnhancingHigh energy proton detector> 10 MeV protonsRange: 10 -500 (1000) MeV5 (10) energy binsSGPS on GOES-R, HET on STEREO NGRML1: MandatoryL5: EnhancingLow & medium energy electron detector30 keV – 8 MeV electrons8 (10) energy binsSEPT on STEREO, NGRML1: EnhancingHigh energy electron detector2-60 MeV electrons1 energy bin > 2 MeV3 energy bins, 1-50 MeVNGRM, HET on STEREOL1: Combination of 6 detectors needed to cover all species and energies. L5: Combination of 2 detectors, NGRM and STEREO SIT.Slide20

Summary

A

dedicated monitoring mission, providing timely observations of conditions on the Sun and in the solar wind, is essential in mitigating against the effects of space weather. Short summary of the assessment of the SWE missions at L1 & L5 is presented, including:

Missions objectives.Analysis and classification of the observational requirements.Space weather mission payload definition. The mission payload is developed in order to accommodate ESA SSA SWE monitoring service requirements.

Acknowledgement: ESA Contract No. 400113189/15/D/MPR, Enhanced Space Weather Monitoring System, ESA's SSA Programme.