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Introduction

SPACEBORNE LIDAR DEVELOPMENTS AT THE EUROPEAN SPACE AGENCY. Introduction. Topics addressed in the presentation ESA Lidar Projects Development strategy Environmental Issues Engineering and Qualification. Earth Obervation Missions. Earth Explorer Research and new Observation Techniques

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Introduction

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  1. SPACEBORNE LIDAR DEVELOPMENTS AT THE EUROPEAN SPACE AGENCY Introduction • Topics addressed in the presentation • ESA Lidar Projects • Development strategy • Environmental Issues • Engineering and Qualification

  2. Earth Obervation Missions Earth Explorer Research and new Observation Techniques CORE missions OPPORTUNITY missions Earth Watch Service-oriented to satisfy operational users

  3. Earth Explorers First cycle: missions selected for Implementation

  4. Earth Explorer plan 06 07 08 09 10 05 11 12 04 02 03 00 01 DEVELOPMENT OPERATIONS CRYOSAT (OPP-1) GOCE (CORE-1) SMOS (OPP-2) AEOLUS - ADM (CORE-2) GCOM-A1/B1 (NASDA) CORE 3- 4 OPPORT. - 2nd ROUND DEVELOPMENT OPERATIONS DEVELOPMENT OPERATIONS DEVELOPMENT OPERATIONS A1 B1 OPERATIONS Call Phase A DEVELOPMENT CORE-3 CORE-4 Call OPP-3

  5. Explorer 2 Second cycle: CORE missions currently in Phase A

  6. Earth Watch Operational Meteorology and Climate Monitoring Oceanography, Atmospheric Chemistry and Global Land/Vegetation Monitoring Surface Monitoring Mission

  7. Optical Payloads

  8. ACE: Instrument Mission Better understanding of Atmospheric Chemistry and Climate Science focus: processes in UT/LS Satellite sun-synchronous orbit, formation with MetOp Core payload: MASTER and advanced MIPAS Enhancements: several additional nadir and limb imagers and sounders, all spectrum

  9. Earth Care Mission Atmospheric cloud-aerosol-radiation interaction Joint European-Japanese mission Evolution of the ERM and ATMOS-B1 Satellite sun-synchronous orbit including: Backscatter lidar Cloud Profiling Radar Multi-spectral imager Broadband radiometer FTS-IR

  10. Earth Care Payload

  11. Core Missions:EarthCARE - Study and development activities Mission definition and performance estimation: 3.2.1 a) CLARA (KNMI - NL) study of synergy of observations, need for co-located observations. Finished 3.2.1 b) Impact of ERM (EarthCARE) observations on NWP (ECWMF - UK) - nearly finished. Interest in NRT data use. System definition and support studies: 2.1.2 b) Pre-phase A of candidate EarthCARE Core Missions, (two studies) Awarded to Astrium (UK). Kick-off is imminent. Second study under negotiation with Alcatel (F) 2.1.3 a) Optimisation of CPR (IPSL-CETP (F) - Impact of new CPR features, 2 frequencies, Doppler shift, multi-beam - HIGH IMPACT ON INSTRUMENT! 2.1.3 e) EarthCARE lidar science objectives (Uni.Leipzig - D) - New lidar features - Starting Instrument: 3.1.1 a) Broadband Radiometer Optimisation Study (SAGEM - F) New BBR concept with ALT scanning. Modelling completed, Concepts established. Trade-off ongoing.

  12. Core Missions: EarthCARE versus ERM Backscatter Lidar Dual-wavelength (1040 nm and 532 nm /355 nm) or single wavelength (532 nm /355 nm) at higher spectral resolution Cross-polarisation channel, multiple field of view, higher radiometric accuracy Higher energy pulses at higher frequency, larger telescope; 300 kg, 270 W, 2.5 Mbps Cloud Profiling Radar Second frequency at 237.95 GHz, duplication numerous elements, tighter requirements many subsystems Extraction Doppler shift - 50 % increase PRF, 4 m antenna Five beams, very large impact at instrument level and avalanche effect at satellite level Multi-Spectral Imager Additional channel 2.2 micron, better spatial resolution (though narrower swath), … larger FPA, mass, power 6-fold increase in data rate Broadband Radiometer Along-track scanning instead of across-track scanning, no significant avalanche effect IR- Fourier Transform Spectrometer New, 70 kg, 100 W, 180 kbps of data. Launch date Near solar maximum!, strong effect of air drag

  13. Core Missions:EarthCARE - Study and development activities Technology: 4a) Cloud Characteristics measurement (RAL-UK) - create data sets and algorithms - as planned 4c) mm- and submm wave open structure integrated front-end (Astrium-D): Schottky diodes delivered 4d) integrated Front-End receivers design and technology (EPF-Lausanne - CH): design review in February 2001 4g) concept of project engineering test bench (GMV-E) - simulation framework, user interface defined 4l) CPR electronic power conditioner (Astrium - D and Alenia - I): testing successful 4m) EIK life-test set-up (CPI-CDN): successful test 4q) development of uncooled bolometer arrays (INO/NOI - CDN) CDR successful, very good performance with EEO-045 4s) Simulator for the engineering and science products of EarthCARE (Open), ITT out 4x) miniature 50 - 80 K pulse tube cooler (Astrium - UK): 800 mW at 80 K, 3 kg, kick-off February 2001 with TRP YCT/04/06

  14. Core Missions: EarthCARE Mission Objectives and Context Objective: Clouds, aerosols and radiation Explorer, building on Earth Radiation Mission and NASDA’s ATMOS-B1 in the post Picasso - Cloudsat time frame Considerably more ambitious than ERM: Higher performance instruments, a new instrument Launch around solar maximum - drag effects at low altitude 350 - 450 km ERM was 1100 kg, Rockot compatible, EarthCARE, 1500 kg satellite Cooperation ESA - NASDA, NASDA providing CPR, IR-FTS and launcher

  15. Core Missions: EarthCARE - Near-term outlook • - General: show mission need in post-Picasso / Cloudsat timeframe • - Watch non-European instruments and consider back-up options • CPR- understand need for CPR enhancements and impact on instrument and avalanche effect on satellite • develop EIK-EPC as ESA is single source and high efficiency LNA • IR - FTS - understand need and utilisation of FTS data, instrument concepts and impact on satellite • prepare key elements also needed for potential European missions, e.g. beamsplitter, mechanismss • (REFIR, W-WISE) • - MMM-981: Magnetic Suspension Based FTS Mechanism • - European instruments: continue optimisation of lidar, MSI and BBR • MMO-622: LIDAR, Ranging and Altimeter Technology • EEO-100: Choice Core Laser Technologies • EEO-045: Uncooled Thermal Imager Array • - Support platform developments leading to lighter, smaller subsystems

  16. Wales Differential Absorption Lidar Accurate profiles of water vapour concentration at high vertical resolution ( 1km in UT/LS) DIAL operated at 940 nm Direct detection technique 1000 profiles per day

  17. Core Missions: WALES - Mission Objectives and Preliminary Concept Objectives: distribution of water vapour and aerosol in upper troposphere and lower stratosphere for research and applications in climatology studies and NWP Achieved by providing globally accurate profiles of water vapour concentration (0.05 - 0.5 g/kg) at high vertical (0.5 - 2 km) and horizontal resolution (10 - 50 km) and with high reliability (95 %). Preliminary concept: Single satellite in sun-synchronous dawn-dusk orbit at 450 km altitude carrying a differential absorption lidar DIAL. DIAL could work in two wavelengths around 940 nm, 435 kg mass, 1 kW power, 60 kbps Satellite: 1200 kg, 1.5 kW, 150 kg propellant

  18. Core Missions:WALES - Study and development activities Mission definition: 2.4.2 b) Evaluation of Spaceborne DIAL for Water-Vapour (DLR - D and OPTECH - CDN) Included under “New Ideas”, transferred to WALES.Requirements analysed for various science areas. Performance models being established. Concepts being defined. System definition and support studies: 2.1.2 a) Pre-phase A of candidate Earth Explorer Core Missions, (together with SPECTRA, ACECHEM and WATS) Awarded to Astrium (D) and Alcatel (F). Kick-off is imminent Instrument: 2.4.2 b) Evaluation of Spaceborne DIAL for Water-Vapour (DLR - D and OPTECH - CDN) - See above

  19. Supporting technology Developments

  20. ADM Aeolus • Aeolus will provide globally wind profiles from 0 - 20 km at 0.5 - 2 km vertical resolution and 1 - 2 m/s accuracy • 800 kg satellite in sun-synchronous orbit, • 400 km altitude • Single line of sight • Sampling scheme: 50 km on a 200 km track • Continuous operation

  21. ADM: Instrument Characteristics Doppler wind lidar, 355 nm, direct detection, Mie and Rayleigh receivers

  22. Technology developemnt For ADM • High Power Pumping Laser Diode Stacked Arrays • 1 kW peak, 150 ms pulse duration, 100 Hz, d.c = 0.25 • 2 Europeans sources identified: TLD and DILAS • Endurance tests (10.000 h): nominal condition (duty cycle: 25 %), • duty cycle 100 %, higher temperature (DT = 20K), higher power (140%) • Radiation tests (p+, g) • Time resolved-measurement ( P(t), l(t)) • Phase Conjugation Mirror (Liquid & Solid) • MPB technologies, CDN • Endurance and Radiation tests on commercial products (liquid cells) • Demonstration of Silica-based PCM

  23. Technology for ADM • High-Efficiency Third Harmonic Generation • Applied Physics Lab. of Bern University • Objective: Get higher than 35 % conversion efficiency • Status: Radiation tests performed on NLO crystals • KTP, LBO and BBO have been investigated • Conceptual design and test set-up design on-going

  24. ADM Laser Breadboard Transmitter breadboard: Objective • Research configuration replicating both the function and configuration of the flight model • Phase I: Laser Test Bed • Demonstration of the full performance on an optical table • Dynamic and Thermal-vacuum testing of pump units, seeder unit(s), Q-Switch and frequency tripler • Phase II: Laser Breadboarding • Packaging of the Laser capitalising on the results of the Laser Test Bed • Thermal-vacuum and limited lifetime testing

  25. ADM Laser UV Breadboard

  26. Injection NPRO Oscillator

  27. UV laser Electronics

  28. LD Laser Pump Module

  29. ALADIN pre-development programme • Main core parallel activities: • ALADIN Pre-Development Model (PDM): breadboard of the Receiver optics, detectors, front-end electronics and the optical bench. (Astrium-SAS) • Laser Test Bed (LTB): breadboard of the Transmitter. • ASTRIUM GmbH and Galileo Avionica • Pump Laser Diodes assessment programmes to check the suitability of commercial laser diodes through lifetime tests and irradiation tests: • CW pump laser diodes (seeder): Innolight and Ferdinand Braun Institute • High power laser diode stacks (power laser): Thales Diodes and Dilas Note: laser diodes are the origin of recent failure of NASA ICESAT laser

  30. Front optics A (FRO-A) Front optics B (FRO-B) Diplexer bread-board Diameter 7.5 mm Diameter 7.5 mm Interference filter (1 nm) Interference filter (1 nm) Fiber Scrambler Field stop Diameter 20 mm Diameter 20 mm Aperture stop Aperture stop l / 2 diameter 36 mm Mie Spectrometer- B (MSP-B) l / 4 Rayleigh Spectrometer (RSP) Rayleigh Spectrometer (RSP) l/4 l / 4 Mie Spectrometer A (MSP-A) thermal control cocoon diameter 4 mm DFU1 DFU1 Detection Front End Units DFU2 Diameter 4 mm Detection Front End Units DFU2 ALADIN PDM: Principle and architecture

  31. ALADIN PDM: integrated configuration A Dual Filter interferometer Front-end Optics Fizeau interferometer Detection front end Unit Detection front end Unit

  32. Laser breadboard I (Galileo Avionica) • To be integrated with PDM for end-to end lidar test (burst mode) • Configuration representative of flight model

  33. Laser breadboard II (Astrium GmbH) To be refurbished for ALADIN airborne instrument (Continuous mode)

  34. Assessment test programme for pump laser diodes (1) • 2 contracts for QCW Laser Diodes • (power laser) • Thales Laser Diodes (baseline FM): • 5500 hours endurance test • 6 stacks still being operated • Irradiation successful • Test in vacuum starts in November • Dilas: • 2000 hours • Numerous stack failures with diode from one source • 2 contracts for CW Laser Diodes • (seeder laser) • Ferdinand Braun Institute (baseline FM): • 3500 hours • Radiation successful • InnoLight: • 2000 hours • Numerous stack failures Conclusions: FM baseline diodes show good behaviour Assessment test results are a good base for a qualification programme

  35. Optical power of Thales stack vs time in burst mode Case Temperature (deg) Optical power (au) Time (hours) Assessment test programme for pump laser diodes (2) Stacked diode bars

  36. Assessment test programme for pump laser diodes (3) Optical Power of the FBH diodes vs time

  37. Studies • Wind statistics • University of Stockholm • Assess wind dynamics and statistics • Impact of measurement errors • In preparation • Analyse impact of errors and their correlations on mission products

  38. Environmetal Effects

  39. Space Environment

  40. Environment • Radiation belts (dominates) • Proton and Electron belts high fluxes • P belt static, e belt dynamic • Solar energetic particles (protons, ions) • Sporadic high flux over short time • Cosmic rays (Fully ionised nuclei, all elements) • Low flux heavy ions • Secondary radiation • Interaction with matter

  41. Anomalous cosmic rays Galactic and extra-galactic cosmic rays Jovian electrons Solar X-rays Trapped particles Incuded emission Solar flare neutrons and g-rays Solar flare electrons, protons, and heavy ions

  42. Radiation Belts

  43. +

  44. Static picture of the radiation belts “Proton Belt”

  45. Static picture of the radiation belts “Electron Belt”

  46. South Atlantic Anomaly

  47. Features of Radiation Belts • Inner belt is dominated by a static population of energetic protons • Proton energies in the range of a few MeVs to hundreds of MeVs • Inner edge is encountered as the South Atlantic Anomaly • Dominates the space station environment • Outer Belt is dominated by a dynamic population of energetic electrons; • Frequent injections and dropouts associated with storms and solar material interacting with magnetosphere (e.g. CME’s) • Dominates the geostationary orbit environment

  48. Static Picture of Radiation Belts “Outer Belt” “Inner Belt”

  49. Standard Radiation Environment Monitor PROBA-1 SREM

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