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JAPAN’s GV Strategy and Plans for GPM K. Nakamura (Nagoya Univ. ) R. Oki (JAXA), M. Kojima (JAXA), and T. Iguchi (NICT)
EO Roadmap - Approach Goals to achieve by prioritization （１）to establish a frequent・continuous observation system through int’l cooperation. （２）to use satellite data for the following purposes －int’l treaty verification, environmental policy, weather forecasting －contribution to improving quality of people’s life Global Warming Monitoring Program prioritizing on “global warming “ which has urgency and necessity ①Greenhouse gas observation mission (observation of materials which causes the global warming) ②Water cycle observation mission (observation of primary effect of the global warming) ③Climate change observation mission （long-term continuous observation of effects of global warming)
Objectives Water Cycle Study and Prediction ①Global water cycle understanding and prediction ②Short-term weather forecast, disaster (heavy rain, typhoon, flood/drought) warning Global, hourly observation of vapor and rain and near-real time delivery of data Observation accuracy improvement Observation・prediction of Rainfall and vapor High frequency observation of Global rainfall and snowfall Observation of tropical rainfall Every 3 hours、0. 2 mm/h
EO Satellite Road Map 2002～ 2006 2007～ 2011 2012～ 2017 Measuring land & sea surface ALOS PRISM（Optical triplet mode, High resolution sensor； Global mapping）： 2 ．5 m PALSAR（L-band Synthetic Aperture Radar； Land information, Disaster monitoring）： 10 m AVNIR-2（Visible & Near Infrared Radiometer： Disaster monitoring etc. ）： 10 m ALOS F/O Geostationary high res optical sensor： 10 m High resolution optical sensor： 0. 5 m Multiple polarization・ Multiple wavelength SAR： 3 m Global monitoring of the Earth’s environment ADEOS-II ILAS-II： Infrared spectrometer GLI ：Visible & Infrared Imager AMSR： Microwave Radiometer Global Water Cycle Observation TRMM Precipitation Radar ： 5 Km, Rain rate： 0. 7 mm/h TMI Microwave Radiometer： （NASA） GCOM-A 1 Land Observations To continuous GCOM-B 1 Green House Gas Monitoring Global Climate Change Monitoring To Operational SGLI ： Visible Land Infrared Imager AMSR F/O ： Microwave radiometer SOFIS： Infrared Fourier Interferometer OPUS： Ultraviolet spectrometer Global Climate Change Observations To continuous GHG Observations GPM To continuous DPR： Dual Frequency Precipitation Radar Water Cycle Observations Earth. CARE CPR：Cloud Profile Radar FTS: Fourier Transform Spectrometer etc.
INITIATIVE OF NASDA TRMM Aqua NASA: Develop the satellite Japan: Develop PR sensor & launch NASDA: Develop AMSR-E NASA: Develop & launch the satellite INPE: develop HSB ADEOS-II NASDA: Develop the satellite, GLI, & AMSR MOE: ILAS-II NASA: Sea. Winds CNES: POLDER GPM NASA: Develop the main satellite Japan: DPR ESA and other agencies: Small satellite NASDA provides satellites data for water cycle research CEOP(Coordinated Enhanced Observing Period) For global water cycle research from 2001 to 2005
GPM Reference Concept OBJECTIVE: Understand the Horizontal and Vertical Structure of Rainfall and Its Microphysical Element. Provide Training for Constellation Radiometers. OBJECTIVE: Provide Enough Sampling to Reduce Uncertainty in Short-term Rainfall Accumulations. Extend Scientific and Societal Applications. Core Satellite • Dual-frequency Precipitaion Radar (JAXA and Ni. CT) • Multi-frequency Radiometer (NASA) • H 2 -A Launch (TBD) • TRMM-like Spacecraft • Non-Sun Synchronous Orbit • ~65° Inclination • ~407 km Altitude • ~5 km Horizontal Resolution • 250 m / 500 m Vertical Resolution Precipitation Validation Sites • Global Ground Based Rain Measurement Constellation Satellites • Small Satellites with Microwave Radiometers • Aggregate Revisit Time, 3 Hour goal • Sun-Synchronous Polar Orbits • 500~900 km Altitude Global Precipitation Processing Center • Capable of Producing Global Precipitation Data Products as Defined by GPM Partners
Sep. 22, 2005 update GPM/DPR development schedule Calendar Year Japanese Fiscal Year (April – March) 2003 2004 JFY 15 1 2 2005 JFY 16 3 4 1 2 2006 JFY 17 3 4 1 2 Milestone 2007 JFY 18 3 4 1 2 3 DRR#1 2008 JFY 19 4 1 2 3 2009 JFY 20 4 1 2 3 2010 JFY 21 4 1 2 3 JFY 22 4 1 2 3 DRR#2 PRR PDR (Ka. PR) DPR Development Ku. PR (JAXA) Component Experiment Reviews in JAXA PDR BBM PQR/PSR CDR (DPR) Prelimi-nary Design Conceptual Design Critical Design Launch Sustaining Design Init. C/ O S/C-system Support EM PFM (Ku. PR) Ka. PR (NICT) * NICT takes charge of Ka. PR EM EM (NICT) Ka Concept Design Ground System Research and Utilization Spacecraft Bus (NASA) PFM (Ka. PR) Ka. PR Preliminary Design 18 months Ground System Investigation Algorithm Development Algorithm Examination RI Algorithm Development Algorithm Examination RA RA RI Oper. T rain Integration & MST Ground System Design & Fabrication Init Cal/ Oper Val Algorithm Test/Improvement, Application and Validation Research and Utilization Investigation Conceptual Design (GSFC) Norm al Opera tion Launch Operation (NASA/JAXA) PFT STM (Ku. PR, Ka. PR) BBM (NICT) 4 Critical Design Preliminary Design PDR FM Fabrication & Assembly CDR Install & Test PQR/PSR PRR: Project Readiness Review, DRR: Development Readiness Review, PDR: Preliminary Design Review, CDR: Critical Design Review, PFT: Proto Flight Test, PQR: Post Qualification-test Review, PSR: Pre-Shipment Review, MST: Mission Simulation Test
Main objective of GPM • To establish accurate and frequent • global precipitation observation system Basic Mission Requirements of GPM (1) To observe the global precipitation (2) To accurately measure the precipitation (3) To frequently measure the precipitation
Design of the GPM Core Satellite and the DPR GMI JAXA and Ni. CT (Japan) : DPR (Ku. PR and Ka. PR), Launcher NASA (US) : Spacecraft, GMI Ka. PR (Spacecraft design by NASA/GSFC) Ku. PR Basic design of Ku. PR and Ka. PR is the almost same as TRMM PR.
Concept of precipitation measurement by the GPM direction core Flight Dual-frequency precipitation satellite radar (DPR) consists of 407 km altitude, -Ku-band (13. 6 GHz) radar : Ku. PR and -Ka-band (35. 5 GHz) radar : Ka. PR 65 deg inclination DPR Range resolution = 250 m and 500 m 5 km GMI 1 38 13 49 1 37 12 Ka. PR: 120 km (24 beams) Ku. PR: 245 km (49 beams) 49
Main Characteristics of DPR Item Ku. PR Ka. PR TRMM PR Active Phased Array (128) 13. 597 & 13. 603 GHz 35. 547 & 35. 553 GHz 13. 796 & 13. 802 GHz 245 km 120 km 215 km Horizontal Reso 5 km 4. 3 km Tx Pulse Width 1. 6 s (x 2) 1. 6/3. 2 s (x 2) 1. 6 s (x 2) 250 m (1. 67 s) 250 m/500 m (1. 67/3. 34 s) 250 m 18 km to -5 km 18 km to -3 km 15 km to -5 km (mirror image around nadir) (mirror image at nadir) VPRF (4000 Hz 250 Hz) VPRF (4500 Hz 250 Hz) Fixed PRF (2776 Hz) Tx Peak Power > 1000 W > 140 W > 500 W Min Detect Ze < 18 d. BZ < 12 d. BZ (at 500 m reso) < 23 d. BZ (Rainfall Rate) ( < 0. 5 mm/hr ) ( < 0. 2 mm/hr ) ( < 0. 7 mm/hr ) Measure Accuracy within ± 1 d. B Data Rate < 108. 5 Kbps < 81. 5 Kbps < 93. 5 Kbps Weight < 370 kg < 300 kg < 465 kg Power Consumption < 350 W < 330 W < 250 W 2. 4× 0. 6 m 1. 44 × 1. 07× 0. 7 m 2. 2× 0. 6 m Antenna Type Frequency Swath Width Range Reso Observation Range PRF Size * Minimum detectable rainfall rate is defined by Ze=200 R 1. 6 (TRMM/PR: Ze=372. 4 R 1. 54 )
Current Status of the DPR Development • DPR is currently being developed by JAXA and Ni. CT. The conceptual design work has almost completed. • JAXA constructed and examined the Ku. PR T/R Unit (Bread Board Model: BBM). We justified the conceptual design and confirmed the possibility of the T/R Unit. • Ni. CT has almost completed to fabricate and is currently examining the Ka. PR T/R Unit (Engineering Model: EM). T/R Unit BBM of Ku. PR
Ku. PR system block diagram Antenna subsystem 001 T/R module 001 SSPA ・・・・ Waveguide slot antenna ・ ・ PHS Harness T/R unit ： ： ： ： ： ： SSPA ・・・・ Waveguide slot antenna ・ ・ ・・・・ Waveguide slot antenna H Y B ＴＤＡ H Y B BPF RＤＡ Frequency Converter and IF System Control Telemetry and Data command Processing Frequency Converter and IF System Control and Data Telemetry command Processing 16 PHS LNA ： ： 128 ・ ・ ・ 127 121 Signal Processing Subsystem CPS 128 LNA SSPA Thermal control 16 Div/comb PHS Waveguide slot antenna Structure 008 LNA SSPA ・・・・ TX/RX subsystem 8 Div/comb LNA ： ： 008 01 S W PHS 8 Div/comb CPS S/C power subsystem
GPM status in Japan • GPM is ranked among future missions in the Roadmap of EO scenario for the new space agency. • Phase B study from JFY 03 was approved by SAC (MEXT) on Nov. 27. Though Ministry of Finance did not approve GPM study as phase B officially, budget and personnel requests were accepted as requested by MEXT. Not an established project, but “quasi-project” in EORC/JAXA. • GPM science team was established in August 2003. • Preliminary evaluation has successfully passed in NASDA (JAXA) in the last August. Next one will be in February/March 2004. • GCOM-B 1: need feasibility study for less constellation satellite case. • Building up International framework is a matter of great urgency for us to request next phase-up and budget by May/June time frame. – The 3 rd GPM workshop was at ESTEC in June 2003. – GPM GV workshop was held in UK in November 2003. – Asia GPM workshop was held in February in 2004.
• GPM Planning Workshop will be held in Tokyo for 7 -9 November • GPM science team • Algorithm development – GSMa. P led by Prof. K. Okamoto – DPR algorithms – High resolution non-hydrostatic atmospheric model – Earth Simulator
Global modelling study Global Cloud Resolving Model: NICAM (Nonhydrostatic ICosahedral Atmospheric Model) Satoh, M. , Tomita, H. , Nasuno, T. , Iga, S. -I. , Miura, H. (Frontier Research System for Global Change) • Use of the Earth Simulator • Δx=3. 5 km grid interval using the icosahedral grid • Nonhydrostatic model with explicitgrid The Earth Simulator Icosahdral cloud physics
glevel-1 glevel-3 glevel-2 glevel-4
Lifecycle experiment of baroclinic waves • Results at day 10 – Temperature & velocity fields at z=180 m Glevel-6 : 120 km Glevel-8 : 30 km Glevel-11 : 3. 5 km