13th european space weather week - stce€¦ · dr. philipp voigt, airbus ds gmbh 17.11.2016 esa...

Dr. Philipp Voigt, Airbus DS GmbH 17.11.2016 ESA Contract No.: 4000113188/15/D/MRP

13th European Space Weather Week Results of the Airbus DS led P2-SWE-X Phase 0 study for an operational SWE Service in L1

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Mission background

The L1 mission

Synergies for a combined L1 and L5 mission and proposed future activities Conclusion

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Content

Mission background



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Study objectives & study team

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• Objective: carry out the analysis for two distinct operational space weather monitoring missions:

– Sun-Earth line mission (“L1”)

– Away-Sun-Earth line mission (“L5”)

– Expected launch: 2023

– Operational lifetime: 5 years

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• full dynamic range not always necessary high sophisticated science instrument not always necessary

• measures to reduce false alarm rate important different kinds of measurements recommended

• SWE events difficult to predict because they can occur at any time 24/7 and 99 % availability required to ensure fast triggering of alarms

• Operational in severe SWE conditions robust design of platform and instruments

• L1 mission has to be fully independent of an L5 mission (and vis versa)

P2-SWE-X - an operational mission

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• Primary objectives: ensure continued availability of the observations of – the Sun

– the solar wind

– the interplanetary magnetic field

• Reasons: – Geomagnetic storm forecasting with

lead times of up to 12 hours (in-situ) and more (Sun observation)

– sufficient to forecast the arrival of a very fast Coronal Mass Ejections with ≤ 18 hour transit time

decide on mitigation actions

Rationale for the measurement baseline of L1

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L1

Effect of the Sun on the Earth magnetic field (image credit: ESA)

The L1 mission



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• Baseline

– One 3-axis stabilized spacecraft in L1 with all instruments to fulfil mission objectives

• Advantages – no eclipse times thus 24/7 availability is

possible with one spacecraft

– pointing accuracy/stability is better than for orbits close to Earth due to the slower drift and the orbit geometry

– Earth is not in the Field of View and no stray light disturbs the observation of the Sun

– best cost/performance approach identified so far

Baseline for L1

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Proposed instrument baseline for L1

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Observation Instrument Type Coronal Imagery for Mapping outer Corona (CME detection) Coronagraph

Interplanetary Magnetic Field Vector Measurements Magnetometer Bulk Plasma Ion Measurement Plasma Analyser Low Energy Ions Ion Detector Energetic Particles Proton and Electron Detector X-ray Flux Measurement X-ray Flux Meter EUV imaging of coronal structures and solar activity EUV Imager Photospheric full-disk magnetograms Magnetograph Imaging of Transients further out of the Sun-Earth Line (HI) Heliospheric Imager

Radio Burst Detection Radio Receivers Optional: NEO images Optional: Telescope

• Sum all instruments: ~135 kg, 195 W, 95 kbps

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• Launch 2023 (2024 as back-up), with Vega-C

• Two main phases – Launch and Early Orbit phase and Transfer Phase

(2-3 months) to L1 including Lunar Gravity Assist with propulsion module

– Operational Phase once at L1 for at least 5 years

• Operational orbit – ‘ACE’-like orbit: Lissajous orbit with an

in-plane amplitude of about 264,071km

– Payloads fully operational and Space Weather data are provided continuously to Ground for supporting the forecasting needs

Launch, transfer strategy & orbit for L1

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ACE orbit evolution and Sun exclusion zone transits (image credit: Caltech)

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• Continuous operation with 99 % availability required

• Baseline: – Dongara, Maspalomas,

South Point: 3 x dedicated 15 m receiving stations for continuous downlink for downloading SWE data (operational phase)

– Cebreros: 1 x 35 m X-Band ESA ESTRACK ground stations for nominal service (telemetry and command) plus downlink of large data volume (e.g. NEO images) – covers small gap in wintertime

Ground stations for L1

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Baseline Back-up

The ESA ESTRACK network (image credit: ESA)

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• One Propulsion Module for the transfer based on the LISA Pathfinder Propulsion Module

• One Science/Operational Module representing the platform

carrying the full suite of SWE payloads composed by two main parts: – A Myriad (Astrobus-S Platform) supplying the required

resources/services of a spacecraft

– An Optic Bench on top of which all the payloads are accommodated

• Many components and subsystems based on heritage (e.g. LISA, SolarOrbiter)

The spacecraft for L1

- 12 -

Synergies for a combined L1 and L5 mission and proposed further activities



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Many synergies for a combined L1 and L5 mission

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• Measurements: synergies identified, e.g.: – Improvement in forewarning times, arrival times and speed predictions – More reliable data sets for modelling purposes – Measurements from different sources resilience

• Instruments: identical set of instruments (except for Ion Detector) Instrument development required only once Cost reduction Decreased effort to calibrate instruments

• Spacecraft platform: platforms are based on existing components with high TRL L1 and L5 could be based on same platform, thus simplify design, procurement and finally integration, testing, launch and operation of both spacecraft

• Launcher: shared launch possible

• Ground station: same ground station concept as proposed but with double shift

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• Miniaturization and robustness of instruments during extreme SWE events (effort vs. benefit to be traded with using existing instruments)

• Several dedicated developments for instruments

• Fix the measurement baseline to ensure dedicated set of instruments before Phase A

• Define timeliness requirements of measurements before Phase A (whole chain from measurements done by S/C, downlink to ground until provision to user)

• Further work w.r.t. measurement/instrument synergies to identify more synergies and to quantify them

Proposed future activities for an L1 and L5 mission (1/2)

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• Consider spacecraft level redundancy like in Earth Observation for better coverage and back-ups in case of S/C loss, e.g. • redundancy within the S/C • several S/C available • international cooperation

• Same applies for ground stations

Proposed future activities for an L1 and L5 mission (2/2)

Conclusion



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Conclusion 1/2

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• System concept has been defined for an operational space-based SWE mission for L1 (and L5) to be launched in 2023 including detailed design

Major Findings • selection of the most important measurements and measurement parameters

to ensure an operational Space Weather mission • Sun observation is mandatory due to early identification of Sun activities and to

have redundant measurements to avoid a false alarm • following instrumentation has been selected

o Coronagraph o Magnetograph o X-ray Flux Meter o Radio Receivers o Magnetometer o Heliospheric Imager o EUV Imager o Proton and Electron Detector o Plasma Analyser o Ion Detector (for L1 only)

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• one three-axis stabilized spacecraft hosting all instruments is the most efficient solution for L1 and L5

• an optical telescope with a 20 cm aperture and a 3°x3° rectangular Field of View is the best candidate for an optional NEO observation identified so far

• many synergies on measurement performance and instrument procurement for a combined L1 and L5 mission have been identified

Conclusion 2/2

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L1 spacecraft in operational configuration L5 spacecraft in operational configuration

Questions!



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Primary • Geomagnetic 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 actions – Identification of the launch of Earth directed CMEs, and their motion away from the Sun,

including the prediction of arrival times at Earth – Provision 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 Earth

– Measurement of vector components of the IMF – Measurement of speed, density and temperature of solar wind – Monitoring of low energy ion precursors of CME shock arrival at Earth – Monitoring of solar energetic particles impacting the terrestrial system – Enable real‐time assessment of Earth‐directed CMEs

Secondary • Monitoring of developing solar activity with potential Earth impact • Provision of stable, continuous space weather data (model development and • underpinning space weather research)

Rationale for the measurement baseline of L1 (credit: ESA)

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Mission Requirements 1/2

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Observation Purpose Priority For L1 For L5

Energetic Particles Early warning of ‘Eastern’ solar energetic particles events (SEP) M* S**

Low Energy Ions Advance warning of coronal mass ejection arrival (CME) M N/A

Interplanetary Magnetic Field Vector Measurements

Input to geomagnetic warnings, forecasts & Geospace models M M

Solar wind bulk velocity Input to geomagnetic warnings, forecasts & Geospace models M M

Solar wind bulk density Input to geomagnetic warnings, forecasts & Geospace models M M

Solar wind temperature Identification of stream interaction region (SIR) M M

*M – Mandatory Payload: Operational mission objectives cannot be met without these data. **S – Study Payload: Impact of data not know yet and has to be studied in more detail (not part of this study).

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Mission Requirements 2/2

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Observation Purpose Priority For L1 For L5

Coronal Imagery for Mapping outer Corona (CME detection)

Identification & triangulation of CMEs (input to models) M M

Photospheric full-disk magnetograms

For L1 and L5: Input to active region classification & magneto-hydrodynamic (MHD) models For L5 ‘White light’ images of solar ‘surface’

M M

X-ray Flux Measurement Flare identification (also available from GOES for Earth-facing disk) M M

EUV imaging of coronal structures and solar activity

Identifying active regions & flare locations M M

Imaging of Transients further out of the Sun-Earth Line (HI)

Continued CME monitoring & forecast/warning corrections S M

Radio Burst Detection CME identification & triangulation when L1 & L5 used in tandem S S

Detection of NEO Detection and tracking of Near-Earth Objects (NEO) Option Option

13th european space weather week - stce€¦ · dr. philipp voigt, airbus ds gmbh 17.11.2016 esa...

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