Remote Sensing via Really Small Satellites: Opportunities and Challenges. Center for Remote Sensing University of Florida January 20, 2012
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1 Remote Sensing via Really Small Satellites: Opportunities and Challenges Norman Fitz-Coy ASTREC Advanced Space Technologies Research & Engineering Center, an NSF I/UCRC Center for Remote Sensing University of Florida January 20, 2012
2 Annual Global Satellite Launches Satellites Launched Orbview-3 (last US Remote Sensing satellite) RS Other Year
3 Remote Sensing Satellites ( ) Year Name Classification Country Description 2009 PRISM Nano (5kg) Japan Amateur/Student 2009 Razaksat Mini (180kg) Malaysia Land man., resource develop 2009 Deimos 1 Micro (90kg) Spain Disaster Monitoring Constellation (DMC) 2009 Dubaisat-1 Mini (190kg) Dubai Optical (2.5m BW, 5m RGB) 2009 DMC-2 Micro (96kg) UK DMC 2009 Sumbandila Micro (81kg) SA Ag. monitoring, disaster response, 2009 Oceansar-2 Big (960kg) India 16 th remote sensing 2010 Tandem-X Big (1350kg) Germany Formation w/ TerraSAR-X 2010 Cartosat 2b Big (694kg) India Optical (0.8m BW), resource man Alsat 2A Mini (116kg) Algerian Resource man, (Alsat 2B later) 2010 Tianhui 1 Chinese 3D mapping 2010 COSMO-Skymed 4 Italian Civil/military reconn (4th in constellation) 2011 Resourcesat-2 Big (1206kg) India Adv. resource man. (water, agri, ) 2011 Haiyang 2 China Microwave radiometer, ocean map 2011 NigeriaSat 2 Mini (268kg) Nigeria DMC, urban planning, 2011 Rasat Micro (93kg) Turkey Multispectral imager,
4 Why Constellations? Improved temporal resolution Spatial distributed observations RapidEye COSMO-SkyMed
5 Small Satellite SWaP Characteristics CubeSats Micro (50 W) Mini (120 W) Pico (2 W) 1kg Nano (20 W) 10 kg 100 kg 500 kg 10 cm ~30 cm ~50 cm ~1 m SwampSat (UF) GeneSat (NASA Ames) UK-DMC2 CubeSat Constraints: Size, weight, and power (SWaP) limit novel configurations/mission Budget (<<$1M per satellite) COTS utilization Development Time Less than 1~2 years development cycle Nigeriasat-2)
6 CubeSat Launches ( ) CubeSats Launched Year SwampSat (2012): On-orbit validation of a 3-axis ACS capable of rapid retargeting and precision pointing of CubeSats using control moment gyroscopes (CMGs).
7 CubeSats as Remote Sensing Platforms CubeSat Paradigm Specialized capabilities Multiple copies with the same specialization (redundancy) Global cross-strapping Individual systems less complex (less expensive) Launch campaign for constitution of constellation BigSat Paradigm Duplication of each component Multiple cross-strapping (redundancy) Complex system (expensive) Limited copies Simpler launch campaign F A F A F 2 F 2 F B F B F 2 F 2 F 2 F 2 F 4 F 4 F 4 F 6 F 4 F 6 F A F B F c F A F B F C F 4. F n F 4. F n F 4. F n F 4. F n
8 Potential Launch Options P-POD NLAS Ecliptic
9 Sample Mission Disaster Monitoring Using Small Satellites
10 Sample Mission Disaster Monitoring: Provide imaging data with a temporal resolution consistent with detection and monitoring Temporal resolution: hourly Spatial resolution: m Constellation of LEO satellites
11 Challenges: Orbit and/or Debris Mitigation 9 satellites 3 planes each with 3 satellites Constellation constitution/maintenance Meets 25 yr. orbital life requirement Safety of ISS (alt. ~400 km) Constellation below ISS Or ensure orbit altitude maintenance
12 Challenges: Resolution vs. Altitude 2.50 Resolution at Nadir (m) D=0.1 D=0.25 D=0.6 D= Altitude (km) r d Pixel of ground element Aperture of dia. D θ Boresight R η Image plane Edge ray target x f h
13 Challenges: Access Area Instantaneous Access Area (IAA) all area potentially visible by an instrument or antenna 30.0 Access Area 25.0 SSP λ (deg) λ max Footprint Altitude (km) Essentially nadir looking
14 Challenges: Constellation Coverage 1 R λmax = cos R + h Sat spacing per plane 2π 2 S = = π N 3 cos λ = cos λ cos S 2 street max ( ) λ max SSP 2 S λ street SSP 1 Street of coverage (continuous coverage) λ max SSP 2 S SSP 1 Continuous Coverage (Street of Coverage) S < 2λ max λ max SSP 2 SSP 1 Limiting Continuous Coverage S S = 2λ max λ max Intermittent Coverage SSP 2 S SSP 1 S > 2λ max
15 Conclusions Technical challenges Attitude control (pointing accuracy ~ 10s of arcsec) Electrical power (OAP ~10s of watts) High bandwidth communication (data rate ~ 50 Mb/s) Onboard computational power (distributed processing) Deployable structures, thermal control (induces pointing disturbances ) Autonomous orbit control (drag compensation) Dedicated launch opportunities Opportunities (launch, mission, ) ELaNa NASA s Educational Launch of Nanosatellites ( NSF CubeSat based Space Weather and Atmospheric Research ( NASA OCT Franklin & Edison Small Sat Program ( GENSO (Global Educational Network for Satellite Operations) Network of university and amateur radio ground stations ( QB50 Network of 50 CubeSats for in-situ measurements in the lower thermosphere ( HumSat Network of small satellites for humanitarian benefits (
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