Remote sensing An Ocean of learning Experiences by DRM Samudraiah Prof Satish Dhawan Scientist,ISRO 9th Dec 2014 Foundation • • Bhaskara TV Payload (1976-1981) First experimental satellite 1Km Resolution, 400kbps, spinning satellite Hi-rel design & development – Pre-amplifier – Video –processor – In charge – all QA interaction • COTS up-gradation & usage – Electro mechanical shutter • P/L integration – Highly complex P/L, frame imaging – Interactions among Optics, Detectors, Electronics, Mechanical and Check-out Instrumentation – High voltage power supply – Life time experience – Noise management – a very tough task – Interface limited system noise performance • Bhaskara-2 Development followed success fully Design of first Operational P/L suite – IRS-1A • • • • • • • • • • • LISS-I & II Development - a great mile stone(1981-1988) Solid state sensor (CCD), push-broom scanning 36.5m resolution, 25Mbps, 3-axis stabilized satellite Realization of perfect systems with engineering precision Custom design based on analysis/ test of Detector New Methodologies/ procedures developed & established Comprehensive design approach for (a) functionality (b) performance (c)reliability (d) manufacturability (e) testability (f) assembly , disassembly & repair Single design for both Cameras but modular to maximize performance. Non-space-grade but state of the art components Quantization limited system noise performance High efficiency: Minimum resources- mass, volume, power and Very few persons IRS-1B/E/P2/P3 followed- Even Eng. Model worked very long High resolution Imaging- IRS-1C • 5.8m (PAN), 23.5m(Mx), 188m(Mx) (1990-1995) • Introduction SWIR band- a great mile stone • High speed detectors had criticalities – optimization of interfaces for best performance • MTF & SNR was very high • New non-space-grade high speed Electronic components • Efficient design & development-Large H/W s • Quantization limited performance with wide band systems. • All payloads worked very well much beyond expected life. India has produced world best civilian sensor of that time. • IRS-1D/ Resourcesat-1- Higher system performance Signal Extraction with Large Variable background • Stringent elecronic noise goal<1 LSB West • Control of detector temperature (100K ±0.1K) East • Optics/structure surface temp. control (0.35K) • Multipath analog processing (~18 bits, using 10 bit ADC) Detector O/P Instances for closing switch •Ground correction using temperature measurements ADC LPF Vds or Vs + Vds Background Signal Bridge Offset 61% 18% Detector Temperatur e Variation Minimum signal Difference Amplifier & Digital to Analog Conversion + stiore GVs + G*e’/G1 e =G1*( Vds - V’ds) 5% Background Variation V’ds=Vds+e 0% 0% 0% 7% 9% G2(Vs + Vds) Difference Amplifier & Digital to Analog Conversion + stiore Vref G1*e + e’ 10 Bits Ocean Colour Monitor – Best in its class - Scaling new radiometric performance (1995-1999) Sensor detected radiance : Lt = Lr + La + t.Lw Lt  Sensor detected radiance Lr  Rayleigh path radiance (molecular scattering) La  Aerosol path radiance (aerosol scattering) Detected radiance (W/cm2/sr/nm) 7 Lw  Water leaving radiance t 6  Atmospheric transmittance  8 spectral bands  Wide FOV- Telecentric  Very high radiometric resolution 5 4 3 2 1 0 412 B1 443 490 B2 B3 510 555 B4 B5 670 765 B6 B7 865 (nm) B8 NOISE MODELLING & Controlling SYSTEM NOISE N (ND * 1.1)= 2460uV True 12 bit system Photon noise limited System performance ELECTRONIC NOISE DETECTOR NOISE ND (2237uV) NE (1025uV) PHOTON NOISE DARK NOISE NDP (2116 uV) NDD( 725uV) COMPONENT NOISE ENGINEERING NOISE NC(418uV) NEG (418uV) POWER SUPPLY NOISE NS(418uV) TES TES (2001)  First very CARTOSAT-1 High Resolution System- 1m Real time stereo viewing Satellite Path  Designed, Developed & launched in 2 years LAUNCHED: 5/05/2005  TDI devices, Large size Invar material & High speed electronic components desirable- Design available components Forewith look Aft look st 26º– 1 step -5º in agile satellite Step & stare Control system  500mm dia optics – Indigenous fabrication  Assembly in 1 g condition for operation in 0 g condition 3D Imagery of Jaipur han 2.5 m resolution n cameras - fore & aft. Tilt m- 850 nm) 27.5 km for stereo and 55 monoscopic mode. erlap between adjacent verlap Cartosat-2 (2007), Cartosat-2A (2009), Cartosat-2B (2010) for across track tilt to tter revisit Cartosat-1 (2005)     First dedicated high resolution stereo mission 2.5m res., 27km swath fore and aft cameras Very high speed Electronics High level of mass optimization- still 250Kg Carto-2: Agile platform Very low mass, 700mm dia mirror- λ/100 surface figure, Indigenous realization Kinematic design for mirror mounts Sub-meter resolution  0.8m res., 9.6km swath  Step-and-stare imaging  Unique imaging modes: spot, paintbrush, multi-view LiV-HySI (Youthsat) Miniaturization RESOURCESAT-1 SNR effect due to Multi-linear Gain  First Indian P/L in limb viewing mode  Sensitivity better than 100 Rayleigh 512 bands RESOURCESAT-2 0.25 Radiance Discriminability per Count LISS 3* B2 Radiance per count RS-1 Improvement due to DPCM coding MIP CAMERA Ruggedized TV camera RS-2 0.20 0.15 0.10 0.05 0.00 53 29.5 19.1 15 10 Radiance Electro-Optical Model LISS-2 A&B (IRS-1A, 1988) IMS-1(2007) Nanosat (2010) Resolution 36m, SWATH- 150Km, Bands - 4 3 Size (cm ) Weight (Kg) Power (W) 229068 150 42 12984 5.8 13 2184 1 1.5 Planned Microsat  1m PAN/ 4m Mx, Swath 12Km  Weight: <25Kg  Size : 0.5 m3 Active pixel detector Wedge filters 3D imager & Single Lens Assembly CMOS SOS Very high resolution – Compact systems for future Carto series SYSTEM STUDIES: SYSTEM REALIZABILITY ACHIEVABLE PERFORMANCE Parameters Carto-2 Carto-2C Carto-3 Eng. Solution 0.8 PAN 0.64 PAN 1.6 MX 0.25 PAN 0.5 MX 5 IR Large telescope –Studies for MTF LIGHT WEIGHTING TECHNOLOGY TDI detector to meet SNR 12000 23084 87000 Optical butting-small array detectors Detector readout rate (Mpix/s) 33 215 1945 Miniaturized, low power high speed electronics/ ASICs Data rate (Gbps) 0.36 VERY HIGH RESOLUTION (m) Total Pixels 41 TDI technology Very high density focal plane Mounting and qualification of strip filters Complex & multiple Focal planes Large size highly light weighted Mirrors High speed, low power miniaturized electronics Orbit (km) 600 550 500 450 400 350 300 0.3 1.6 TB storage, Data Compression, Custom data acq. & test bench, Tx Challenges Dia: 1.2m Focal length 17.5 m, Orbit 600 km Optics MTF vs diameter Light Weighting 80% Dia & Focal length adjusted for same SNR & MTF Detector Dwell MTFdiff Focal Aperture Focal Time Signal (optics) Signal Payload Length (in m) Length (µsec) (relative) at (relative) Weight (m) (m) Nyquist (normalized) 36.22 1 0.24 19.2 1.2 19.2 1.00 1.00 35.83 1.17 0.29 17.6 1.1 17.6 0.99 < 0.84 35.44 1.41 0.34 16 1 16 0.98 < 0.69 35.06 1.72 0.41 14.4 0.9 14.4 0.97 < 0.56 34.67 2.15 0.47 12.8 0.8 12.8 0.96 < 0.44 34.29 2.78 0.53 11.2 0.7 11.2 0.95 < 0.34 33.91 3.75 0.59 9.6 0.6 9.6 0.94 < 0.25 Diffraction limit vs Diameter 0.25 MTF @ 57 lp/mm • • • • • • 4 MTF vs diameter of primary mirror 0.2 0.15 0.1 0.05 0 700 750 800 850 900 950 1000 1050 1100 1150 1200 Mirrror diameter (mm) ESTIMATED SYSTEM PERFORMANCE D1R1 Developments Realized for Carto-3 1143 lines D1 D1R3 29 lines D3R1 D3R3 D3 530 pixels 511 pixels 1130 lines 450 pixels D2R1 D2 D2R3 Satellite Motion D1 20 Pixels Overlap D2 D4R1 D4 D4R3 TES CONFIGURATION D3 D4 Satellite Motion PROPOSED DETECTOR BUTTING Realizations helped in advancing TDI technology to Carto-2C In House 3Dstacking  TDI Electronics  Second & third miniaturized version Resolution(m) 0.43@450Km Detector readout(MHz) 18 SNR@Saturation >400 Data rate (Mbps) 1120 Power(W) 5.3 Size(mm3) 48*89*60 Weight(gm) 200 FIRST DEVELOPMENT 1.43 Kg, 8.5” X 4.5” X 3.5” Detector response ASICs Enhancement of GEO imaging – INSAT-3D Scan mirror INSAT 3D-weather satellite (2nd in the world) VHRR VIS. 2KM No MIR Broad WVP 8KM Broad TIR 8KM -Complex scan mechanism 3D IMAGER VIS. 1KM No SWIR SWIR 1KM Satellite Path -Synchronization complexity VHRR TIR:8KM -Miniature Electronics Radiation from ground Ground coverage Ground resolution element MIR 4KM Narro w WVP 8KM 3D TIR:4KM Split IMPROVED TIR:1 TEMPORAL 4KM RESOLUTION for Split half hourly Full disc TIR:2 by cutting Space view 4KM 2X Spectral and Spatial New SOUNDER P/L for Resolution Improvement vertical profile, 1st over over VHRR (K1, 3A) Indian Ocean IMAGER Flight Model 19 Channel Sounder for INSAT 3D Earth emitted spectra overlaid on Planck function envelopes O3 CO2 H20 CO2 GISAT Payloads High Resolution Imaging Sensors on GEO Platform Improved Imaging Capability Current(VHRR) New (GISAT) VNIR 1000m GSD TIR 8000m 1Band HySI (VNIR / SWIR ) NIL 250Ch ~50 m GSD 6 Ch ~1500 m MX 6 Ch ~320 / 192 m 400 Ch • Large mirror • IR imaging technologies • Asynchronous formatter • CCSDS standard • Eficient, high power cooler drive electronics for 50K detector operating temperature • SNR > 1000 @ 6MHz readout rate GISAT-MIR Area Array Outdoor Imaging IR detector + cooler Human Spaceflight Programme  Mission duration up to 7 days  Emergency mission abort and crew rescue provision during ascent and orbital phases of flight  Capability to maneuver in atmosphere  Crew module lands in sea or in land mass with velocity ~ 2 m/s Environmental Monitoring System CREW CABIN LIGHTING Oxygen, CO2, CO, CH4,Temperature, pressure & humidity sensors Oxygen Meter Thermometer Interface Status Indicator Display System Altimeter LED based 30230lux, 12m2 area Chandrayaan-2 Chandrayaan-1 TMC-2 further miniaturized w.r.t TMC-1, weight reduced by 1/3rd Centralofpeak ofhalo Tychocraters crater Remote Sensing Dark TMC data 2 TMC (Stereoscopic Imaging) Spatial sampling 5m Swath 20km Raw Power <5W (TMC1 – 7.7W) Weight 4 kg (TMC1 – 6.3kg) 1 1, 2 : Evidences of Volcanism on Central peak Of Tycho Crater using TMC data Rover Camers Power Camera head Weight Size:49mm X 22mm < 2W < 40g HySI image, 64 VNIR Bands of lunar craterlet IIRS (Mineralogical Mapping) (0.4 to 5µ) Spatial sampling Along track 80m Across track 40m Swath Raw Power 20km <20W Weight 6.5 kg Hazard Detection and Avoidance Sensors for Lander 0.25m hazard detection - Orbiter High Resolution Camera (OHRC) On Lander : Position Detection and Hazard Detection cameras for autonomous navigation TMC-1 5m Stereo triplet Mars Orbiter Mission  Three Electro-optical Payloads delivered – Concept To Delivery < 1.5 Year Concurrent Engineering Multi-model- co-development COTS Ruggedization & Miniaturization Unique ways of confidence building Exemplary ways of motivation Thermal Infrared Very high levels of dedication Imaging Spectrometer 1K NEΔT Mass (kg) 2.94 Power (W) 7.5 Mass (kg) 3.2 Power (W) 6 Mass (kg) 1.3 Power (W) 3 Mars Colour Camera Methane sensor for Mars Ppb Accuracy VHRR 3D IMAGER& SOUNDER OCM LiV HySI CHANDRAYAN-1 MARS MISSION Sensors developed to observe earth (land, ocean, atmosphere) and planetary from space in various wavelength bands PANCAMERA Cartosat-2B 2010 Bhaskara 1979 1km 1km Bhaskara From a Kilometer to a Meter MOON 360m 360m 17-Apr-14 188m 188m <1m <1m 2.5m 2.5m 23m 23m 5.8m SAR 56m 56m 6 VIDEO SIGNAL PROCESSING- EVOLUTION 4.5E+8 CARTO-2C 2014 4.0E+8 Processing (Pix/s) 3.5E+8 3.0E+8 2.5E+8 2.0E+8 1.5E+8 1.0E+8 5.0E+7 CARTO-1(2004) RESOURCESAT2 (2011) IMS-1 (2007) 1.0E+0 BHASKARA (1979) OCM (1999) 5 10 15 Digitizer (Bits) MARS (2013) 20 HSP- ECLSS (2017) 25 NER nW/str/um/cm2 1E+5 1E+4 1E+3 1E+2 1E+1 1E+0 Radiometric performance - Evolution Efficiency Analysis – Payloads Acknowledgement: Team ISRO Thanks ISRS