Developments Towards a Spacebased Wind Lidar for the International Space Station

Transcription

1 Developments Towards a Spacebased Wind Lidar for the International Space Station Carl Weimer & Sara Tucker Ball Aerospace & Technologies Corporation Mike Hardesty CIRES 4/15/2016

2 What Is ATHENA-OAWL (A-OAWL)? Earth Venture Instrument 2 (EVI-2) Proposal to NASA in 2013 Not Selected for space mission Category 3 Was selected for Earth Venture Risk Reduction Funding ( Venture Tech ) to advance its Technology Readiness Was Led by PI Lars Peter Riishojgaard University of Maryland (now WMO) Now led by Mike Hardesty (CU/CIRES) Ball Aerospace is the Instrument Provider Doppler Wind Lidar based on the OAWL technique Focused Science Mission Tropospheric dual Line of Sight Winds plus aerosols Earth Venture Instrument is Cost Constrained Design to Cost $94 M with 25% reserves Uses International Space Station (ISS) and its Mission Operations, and TDRSS downlink Met the WMO requirement for < 3 m/s precision, < 0.5 m/s bias Earth Venture is for NASA Class C (Medium to Low Complexity) Leverage Heritage Designs from CALIPSO and other Instruments One Year Lifetime

3 Progress Against Plan Upgrade existing OAWL instrument to match the ATHENA-OAWL two-look, two laser configuration New aircraft testing on the WB-57 adding in additional balloon and drop sonde comparisons for wind validation for different atmospheric conditions (Eight flights completed, approximately 45 dropsondes Sara s talk) Will also include comparisons with AERONET, HRRR, etc for aerosol calibration (In process Sunil s talk) ) Complete qualification for space environment of key new technologies Green (532 nm) only lifetime testing of the HEUVD laser at Fibertek (Complete - Floyd s talk) Perform thermal/vacuum testing of the new athermal interferometer (In fabrication below) Parallel Effort HAWC-OAWL (PI Sara Tucker) is funded by NASA ESTO to develop a dual-wavelength HSRL/Wind version of OAWL for atmospheric transport and Chemical Weather (In process)

4 Athermal Interferometer in Development Being Built to Aerospace standards 4 6/30/2016

5 Structural Model and Analyses are complete Includes evaluation of modes and deformations Ensuring that we survive launch Beam splitter example colors give magnitude of deformation during launch loads Page 5

6 Thermal deformation study complete Structural-thermal modelling used to verify athermal design will ensure interferometer alignments for ISS environment 6 6/30/2016

7 Overall Lidar System Start from CALIPSO Heritage Design and Simplify EV-I Constraints Deployment to ISS Simplify from Heritage Design to Cost

8 Update Design for New Application and new platform Winds from ISS 8 6/30/2016

9 CALIPSO Laser Performance 10 Years on Orbit Second Laser Performance Shown. - both 1064 nm and 532 nm Slow energy drop is due to degradation in the pump diodes Expect to operate through 2017 (12 year lifetime, 3 Year Mission) ATHENA-OAWL will be 532 nm only with same laser eye-safety margins

10 Vibration Comparison - Operational Core engineering principle is Design and Test as flown - i.e. for the launch and operation environment Requires detailed knowledge of the environment Requires the funding for the engineering and test facilities Note - Launch vibe is off this scale 10 6/30/2016

11 Temperature Comparison WB vs CALIPSO Optical Benches (both passive) CALIPSO has a gradient but variations are < 1 C WB 57 bench depends on tarmac time, flight profile, and conops Two WB Flights CALIPSO 11 6/30/2016

12 Lidar Receiver Electronics Path to Space Designed/Built on AOVT and have space-qualified equivalents (below) Detector replaced by qualified PMT - Heritage Replaced by an update of Ball s Common Instrument Controller Electronics now qualified for TEMPO Board Function HAWC/AOVT Part Space Part 12 Detector TIA AD8001 AD8001S Detector & APB Amplifier AD8139 AD8138S APB High-Speed ADC ADC14155 ADC14155QML-SP APB FPGA XC5VFX130T XQR5VFX130 6/30/2016

13 Conclusions ATHENA-OAWL can act as a Pathfinder towards the full 3D-Winds mission Demonstrate the science capability with immediate (< 1 hour) data availability to Numerical Weather Models Validate the laser and receiver performance in the space environment Through the NASA Venture Technology program, significant risk reduction to the proposed effort is now occurring The effort will be bid again to the Earth Venture Instrument call, which will likely be the last time ISS will be available for EV missions due to the planned 2024 end date of ISS 13 6/30/2016

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