Minimize RADARSAT-2

RADARSAT-2

RADARSAT-2 is a jointly-funded satellite mission of CSA (Canadian Space Agency) and MDA (MacDonald Dettwiler Associates Ltd. of Richmond, BC), representing a Canadian government/industry partnership [or PPP (Public Private Partnership)] in a commercial venture. In Feb. 1998, CSA awarded a contract to MDA to built RADARSAT-2. The contract calls for MDA to develop, own and operate RADARSAT-2 and related infrastructure (including data distribution). CSA provides a fixed financial contribution to MDA (about 75%), in exchange for imagery allocation from the S/C to government agencies. Also, ORBIMAGE, an affiliate of Orbital Sciences Corporation (OSC), Dulles, VA, is a significant participant in this program as the exclusive distributor of RADARSAT-2 imagery to U.S. customers. 1) 2) 3) 4) 5) 6) 7) 8) 9) 10) 11) 12)

US space policy, regulations related to the export of satellite and rocket technology as well as to the distribution of high-resolution imagery, caused CSA in January 2000 to cancel an existing satellite bus contract with OSC (Orbital Sciences Corporation) of Dulles, VA, and to award a new contract to Alenia Spazio of Rome, Italy.

RADARSAT-2 is an advanced state-of-the-art technology follow-on satellite mission of RADARSAT-1 with the objective to:

• a) continue Canada's RADARSAT program and to develop an Earth Observation satellite business through a private sector-led arrangement with the federal government

• b) provide data continuity to RADARSAT-1 users and to offer data for new applications tailored to market needs.

• c) the key priorities of the mission respond to the challenges of:

- Monitoring the environment

- Managing natural resources

- Performing coastal surveillance.

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Figure 1: Overview of the RADARSAT-2 development structure (image credit: MDA)

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Figure 2: Artist's rendition of the RADARSAT-2 satellite in orbit (image credit: MDA)

Spacecraft:

The S/C consists of a bus module, a payload module, and the ESS (Extendible Support Structure). Alenia Spazio, EMS Technologies, and AEC-Able were respectively awarded the subcontracts (from MDA) for the spacecraft bus, payload, and ESS. The SAR antenna itself is supported by ESS, which is used to deploy the antenna and to provide a rigid support in the deployed position. Note: As of 2006, the former EMS Technologies Canada Ltd. was bought by MDA and is now referred to as MDA Space Systems.

The S/C bus is based on PRIMA, a reconfigurable bus developed for the Italian Space Agency (ASI) with bus dimensions of 3.7 m (height) by 1.36 m (diameter). The phased array SAR antenna, built by EMS of Montreal, has 8192 radiating elements fed by 512 T/R modules, two subapertures are provided offering a limited GMTI (Ground Moving Target Indication) capability based on along-track interferometry. The overall SAR antenna size is 15 m by 1.5 m with a mass exceeding 700 kg.

The S/C is three-axis stabilized (zero-momentum satellite). ACS (Attitude Control Subsystem) is using two star trackers for precision pointing (provided by Galileo Avionica S.p.A. of Milan, Italy). Attitude knowledge is ±0.02º, attitude control is ±0.05º (3σ in each axis). The GPS receiver (LAGRANGE of Laben SpA) provides real-time position knowledge of ±60 m. Image location knowledge is < 300 m at downlink, and < 100 m for processed imagery. RADARSAT-2 is yaw-steered (unlike RADARSAT-1). The yaw steering, combined with the improved attitude control of RADARSAT-2, simplifies image processing and improves image quality. Yaw steering provides a measure of Earth rotation compensation and thus brings the data Doppler centroids (DC) near zero Hz. 13) 14)

S/C mass at launch is 2200 kg, power of 2.4 kW at EOL (two solar panels with dimensions: 3.73 m x 1.8 m, each), one Nickel-hydrogen battery with 89 Ah. The S/C design life is seven years. RADARSAT-2 provides several new imaging modes, such as polarimetric imagery (retrieval of full vectorial polarization information), ultra-fine (3 m resolution) beams, in addition to preserving all RADARSAT-1 modes.

RADARSAT-2 uses a monopropellant hydrazine fuel. The S/C has six 1 N thrusters which are used initially to manoeuver the spacecraft into its operational orbit (correcting any launch dispersions). The thrusters then maintain the spacecraft's orbit to keep the ground track within a strict tolerance range (better than ± 5km, with a goal of ± 1km) during its operational lifetime.

Parameter

RADARSAT-1

RADARSAT-2

S/C mass at launch

2750 kg

2200 kg

Design life

5 years

7 years

Onboard data recording

Tape recorder (analog)

Solid-state recorder (384 Gbit) and addressable data retrieval

Spacecraft location (tracking)

S/C ranging from ground

GPS receiver onboard

Imaging frequency

C-band at 5.3 GHz

C-band at 5.405 GHz

Spatial resolution of data

10-100 m

3-100 m

Polarization

HH

Fully polarimetric

Switching delay between imaging modes

about 14 seconds

≤ 1 second

Look direction of SAR antenna

Right

Left or Right (faster revisit times)

S/C attitude control

Sun sensors, magnetometers, and horizon scanners

Two star trackers for precision pointing

Downlink power transmitter

Standard ground antenna size of about 10 m diameter is needed

Ground antenna size of 3 m diameter is needed

On-board location accuracy device

None

GPS receivers (± 60 m real-time position information)

Yaw steering

None

Yaw steering for zero Doppler shift at beam center (facilitates image processing)

Table 1: Comparison of RADARSAT-1 and -2 system capabilities

 

Launch: A launch of RADARSAT-2 took place on Dec. 14, 2007 on a Soyuz launch vehicle (launch provider: Starsem) from Baikonur, Kazakhstan.
Note: Initial arrangements were made in 2003 with the Boeing Company to launch RADARSAT-2 on a Delta-2 vehicle from VAFB. However, after the arrangement was made, there were objections from US intelligence agencies who felt the S/C observations would pose a threat to US national security.

Orbit: Sun-synchronous polar orbit, mean altitude = 798 km, inclination = 98.6º, period = 100.7 min (14 7/34 orbits/day), LTAN (Local Time on Ascending Node) = 18:00 hrs ±15 min (dawn-dusk orbit), repeat cycle = 24 days. RADARSAT-2 is in the same orbit as RADARSAT-1, separated by 30 minutes (and having the same ground track and repeat cycle as RADARSAT-1). The spacecraft orbit control system is capable of maintaining ground-track repeatability to within at least ± 5 km (with a goal of ±1 km), at any point in the orbit. This facilitates proper ground station scheduling. In addition, the tandem flight configuration of RADARSAT-1 and -2 provides a wealth of interferometric applications support.

Orbit determination: The POD (Precise Orbit Determination) software in combination with the onboard GPS receivers permits accurate real time orbit information. The LAGRANGE receiver is a 12-channel dual frequency receiver that produces pseudorange and Doppler phase measurements. The POD software is a GPS based onboard orbital filter, which uses an orbital filter to combine the GPS measurements with high fidelity orbit models to significantly improve onboard orbit knowledge, under the constraints imposed by the bus on the onboard computing resources. Fast-delivery position knowledge is ± 60 m (3σ in each axis), the post-processed position knowledge is ± 15 m (3σ in each axis). 15)

RF communications: Two onboard SSR (Solid-State Recorder) each with a capacity 150 Gbit BOL provide recording of the source data outside of the receiving station range. They can accept data at rates up to 400 Mbit/s. BAC (Block Adaptive Quantization) data compression is used to encode signal data with a selectable wordlength (normally 4 bits I + 4 bits Q).
Payload downlink of two parallel X-band channels at 105 Mbit/s for real-time data reception. Encryption is available for command & control as well as for the downlink of signal data. S-band for TT&C communications: downlink data rates at 15, 128, 512 kbit/s (2230.00 MHz), uplink data rate at 4 kbit/s (2053.458 MHz).

Agreements between CSA and MDA make MDA the S/C owner and operator. The RADARSAT-2 ground segment is also owned and operated by MDA. This includes the re-use of the existing RADARSAT-1 infrastructure where possible. CSA's investment will be recovered through the supply of imagery to a number of Canadian government agencies during the mission lifetime. RSI (as well as others) are a commercial distributors of imagery.

 


 

Mission status:

• The RADARSAT-2 spacecraft and its payload are operating nominally in 2014. On Dec. 14, 2013, RADARSAT-2 completed 6 years on orbit.

• December 13, 2013: MDA’s Information Systems group announced that it has signed an agreement with the European Space Agency (ESA) to provide RADARSAT-2 information to user groups under ESA’s Third Party Mission Program. The RADARSAT information will be used to perform research and develop applications and services such as ice monitoring, pollution monitoring, disaster management, agricultural monitoring and forest management. 16)

• October 21. 2013: MDA announced that it has signed two contracts for the provision of RADARSAT-2 information and services. 17)

- The Norwegian Space Center has extended the contract, signed in January 2003, for MDA to provide RADARSAT-2 information to the Norwegian government for a further three years for use in ice mapping, landslide monitoring, oil spill detection, and ship detection services.

- The second contract is an amendment for MDA to extend its provision of RADARSAT-2 imagery until November 2014 in support of Europe's Copernicus program. The RADARSAT-2 imagery will be used to provide mission critical information for sea ice monitoring of the Baltic Sea, Arctic Ocean, and Antarctic Ocean throughout the ice seasons, improving the safety of maritime navigation and supporting environmental monitoring as part of the Copernicus program.

• The RADARSAT-2 spacecraft and its payload are operating nominally in 2013. 18)

• 2012: DRDC (Defense Research and Development) of Ottawa Canada, and Fraunhofer FHR (Wachtberg, Germany) are developing new operation modes and signal processing methods to enhance and optimize the traffic monitoring capability of the satellite RADARSAT-2.This method enables efficient detection of moving objects and accurate estimation of their parameters and does not require any knowledge of the street network. 19) 20)

• On July 20, 2012, the operator of RADARSAT-2, MDA (MacDonald, Dettwiler and Associates Ltd.) announced that it had signed a contract amendment with CSA and ESA to increase its provision of RADARSAT-2 satellite imagery to Europe’s GMES (Global Monitoring for Environment and Security) program. The additional RADARSAT-2 imagery addresses the gap in data availability created by the recent loss of ESA's Envisat spacecraft in April 2012. The agreement fulfills ESA’s maritime monitoring needs until the full operational capacity of the Sentinel-1A satellite is available, which is expected around mid-2014. 21)

The RADARSAT-2 imagery will be used to provide mission critical information for sea ice monitoring of the Baltic Sea, Arctic Ocean, and Antarctic Ocean throughout the ice seasons, improving the safety of maritime navigation and supporting environmental monitoring as part of the GMES program. GMES was established to provide users in Europe with access to accurate and timely information services to better manage the environment, understand and mitigate the effects of climate change and ensure civil security.

• The RADARSAT-2 spacecraft and its payload are operating nominally in 2012. RADARSAT-2 has now completed four years of routine phase operations. A thorough mid life review of all spacecraft subsystems has been completed. The spacecraft and ground segment continue to perform well and the operations team strives for best achievable performance. 22)

Some performance items of interest are listed below:

- System outages: A transient event (SEU) caused a malfunction of one of the gyroscope in March 2012. The transient caused an attitude divergence, leading to a Processor Module (PM) restart. Payload and many bus units were switched off resulting in several hours recovery. This anomaly had been observed by the manufacturer on another spacecraft.

- Satellite operations: The frequency of orbit maneuvers to maintain a ±500 m ground track have recently increased from once every 1.5 months to once every 3 weeks due to higher solar activity (more drag). The burn frequency is expected to increase in relation with solar max activity in 2013. Burn activities are conducted without impact on payload activities. Slew maneuvers from right looking to left looking and back are performed in average 150 times a month. - Two collision avoidance maneuvers were performed to prevent risk of collision with other objects. One without user impact, the second one required a few hours outage to perform a retro burn in order to maintain the ground track.

- Alternate downlink: During the peak activity season of summer 2011, bottle necks were identified in the overall downlink time available with the Canadian receiving stations. The current GS systems only allow a user to specify a single downlink location [e.g. Gatineau Receiving Station (GSS)]. The change introduced with the alternate downlink project would let the user specify up to four alternate sites to downlink the data (e.g. Gatineau Station or Prince Albert Station), thus introducing more flexibility for the planning system to find the earliest downlink opportunity and improving the overall downlink capacity usage.

- New and Enhanced Beam Modes: Mode development continues with the next mode in line being, Extra Fine. The mode will offer the best compromise between wide swath (105 to 170 km), and resolution (5 m). New product types offering different resolutions and number of looks from the same mode are being made available. - Work is in progress to extend the coverage offered by Ultrafine and Spotlight from 49.54º to 54.2º, bringing the range resolution down to 1.9 m.

- PDHT timeouts: One of the recurring payload anomalies used to be a timeout issue that occurs at end of imaging and results in a partial lost image if the image is taken in pass through mode (downlink occur while the satellite is still imaging). In depth investigation has been carried out, and changes made to reduce the occurrence of such issue. The result shows a decrease of occurrence by about 40 %. Only a few modes are still occasionally affected and effort to reduce the impact is continuing (Ref. 22).

• August 18, 2011: Imagery acquired from the Canadian satellite RADARSAT-2 has enabled the landmark discoveries announced today by UCI (University of California at Irvine) researchers. - Previously unmapped glaciers of Antarctica have been charted by accessing imagery collected from Canadian, European and Japanese satellites. Using NASA technology, the researchers have discovered unique terrain features that indicate the direction and velocity of ice in Antarctica. This will provide invaluable insight into ice melt and future sea rise due to climate change.

The full continental coverage of Antarctica was made possible due to the unique capabilities of RADARSAT-2 to image left and capture data and information over the central part of the continent. This capability allowed the capture of data over the full land mass, from the South Pole to the coast, imagery that is at the heart of the discovery made by the UCI researchers (the project was funded by NASA). 23) 24) 25) 26)

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Figure 3: First map of ice velocity over the entire continent of Antarctica derived from radar interferometric data, (image credit: NASA/JPL, UCI, ESA, CSA, JAXA)

Legend to Figure 3: The map is mainly derived from Envisat, Radarsat-2 and ALOS SAR data, with some contribution of ERS-1/2 and Radarsat-1 data. These new findings are critical to measuring the global sea-level rise resulting from ice flowing into the ocean. The Antarctica ice velocity map is based on SAR data acquired during the International Polar Year (IPY 2007-8) in coordination between ESA, CSA and JAXA. The map, which was created by scientists from the University of California Irvine and NASA's Jet Propulsion Laboratory, reveals not only the flow of the large glaciers, but also their tributaries – effectively rivers of ice – that reach thousands of kilometers inland. 27)

The color-coded satellite data are overlaid on a mosaic of Antarctica created with data from NASA's MODIS (Moderate Resolution Imaging Spectroradiometer) instrument on the Terra spacecraft. The pixel spacing is 300 m. The thick black lines delineate major ice divides. Subglacial lakes in Antarctica's interior are also outlined in black. Thick black lines along the coast indicate ice sheet grounding lines (NASA/Caltech-JPL).

• In Sept. 2011, MDA signed a contract with the US NGA (National Geospatial-Intelligence Agency) to provide SAR data (of RADASAT-2) to be used in creating ice charts and for maritime surveillance to improve the safety of maritime navigation. 28)

• In the summer of 2011, RADARSAT-2 has completed over three years of routine phase operations. The spacecraft and ground segment continue to perform well and the operations team have successfully implemented a number of system enhancements and improvements. 29) 30)

- The system outage history for the last two years of Routine Phase operations is shown in Figure 4. The above 97 % availability requirement has been consistently maintained. Despite the growing demand of RADARSAT-2 SAR data, the success rate of the image acquisitions has been maintained at a high level.

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Figure 4: System outages in the period March 2009-March 2011 (image credit: MDA, Telesat)

- The RADARSAT-2 spacecraft has continued to meet performance specification with margin throughout the Routine Phase. There have been no unusual trends in the spacecraft bus subsystem performance. The battery performance in the annual eclipse season has been nominal with battery depth of discharge of less than 8% of the battery capacity.

- During the last year there have been outages caused by recurring anomalies, a few with new signatures, and also some new anomalies with the payload sensor electronics, some of which caused loss of images. Many of these new anomalies are self recovering. These anomalies have been generally attributed to SEU (Single Event Upsets) and managed through monitoring and recovery using pre-prepared and, in some cases, automatic recovery procedures. - As the solar activity rises towards the maximum in the cycle, the rate of SEU occurrence will continue to be monitored, and the management measures will be modified and enhanced, if necessary, to minimize performance impacts.

- The image quality has been maintained or improved in all aspects over the last year of operations. The performance monitoring campaign, to track systematic variations in the system, and to apply periodic updates to various calibration factors, which was established in the beginning of operations, is continuing and has allowed identification of issues and potential performance enhancements, and for adjustments, in addition to the seasonal adjustment to the calibration factors.

- The RADARSAT-2 image quality function is closely coupled with overall system maintenance and the resolution of problems appearing at system level. As examples, the occasional appearance of darker bands in the VV channel of some ScanSAR images has been resolved through payload configuration adjustment. The tracking of intermittent abortion of image data downlinks has highlighted some critical factors in the timing of the acquisitions and has been addressed through beam-modes adjustments. The development of experimental modes triggered a particular SAR payload behavior which caused inconsistent beams in some highly specialized ScanSAR modes. This behavior is now characterized and beam consistency achieved through beam design.

- RADARSAT-2 mission planning has been at the forefront of several ordering and planning system improvements to continuously improve the RADARSAT-2 ordering experience and to optimize the use of the satellite resources. Some of the key improvements made over the last year include:

1) Feasibility checks function now available from the Acquisition Planning Tool (APT).

2) Order desk template functionality to streamline order creation for customer with repeated order parameters.

3) Acquisition and Reception Planning Software (ARPS) upgraded to allow sharing of the same reception segment between two stations with overlapping mask.

4) System upgrades to support the development and operation of HMA (Heterogeneous Mission Access) interface with ESA. The catalog service interface has been completed.

5) Implementation of the ordering capabilities of several new or updated versions of beam modes.

- New network (receiving) stations were added to give a total of 12 foreign partners operating 22 X-band receiving antennas.

- As of March 2011, RADARSAT-2 has now completed 42 orbit maintenance maneuvers. One collision avoidance maneuver was performed in June 2010, followed by a retro grade burn to keep the ground track within its operational target bounds.

- Figure 5 shows an overall growth in data acquisition over the last year, split between government and commercial users, and also the remaining background and image quality/calibration acquisitions. On average over 4,200 acquisition segments have been programmed per month over the last year.

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Figure 5: Minutes of acquisition time used by major user group (image credit: (image credit: MDA, Telesat)

- Satellite operations: While orbital collision risk is still assessed to be low, the Iridium/COSMOS incident in 2009 has increased the risk and made LEO satellite operators more aware of the need to adopt mitigation strategies. RADARSAT-2 satellite operations continues to pay increased attention to orbital collision avoidance and the incorporation of collision avoidance procedures into the operations.

Naturally, the RADARSAT-2 project is taking advantage of information and services available from national and international agencies. The inputs feed the collision avoidance procedures, which include quantitative criteria for avoidance maneuver planning. RADARSAT-2 is working with CSA, and the RADARSAT-1 mission, to refine the procedures and tools for risk assessment and avoidance maneuver decision.

- Antarctic mosaic: As a successor to the RADARSAT-1 Antarctic Mapping Mission (AMM) in 1997, and as part of the International Polar Year, the continent was imaged to provide Pole to coast dual polarization mosaic coverage and 3 cycles of interferometric coverage for ice velocity mapping of the interior. RADARSAT-2’s agility to slew to “left-looking” to avoid the coverage gap beyond 78º S in the normal “right-looking” orientation was used extensively with 620 slews for the mosaic campaign and 570 slews for the interferometric coverage.

Satellite slewing between the imaging orientations involves a 10 minutes imaging outage for the maneuver and stabilization. So as to minimize the impacts on other users, the satellite slew constraints and the planning were reviewed and modified. Better than specification in-orbit performance permitted the satellite slew constraints (number per orbit) to be relaxed. Planning for command uplinks and slew timing were arranged to allow for the greater command volume and to minimize conflicts.

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Figure 6: RADARSAT-2 Mosaic of Antarctica (image credit: MDA. Telesat)

- Enhancements for Project Polar Epsilon: Under the Canadian Department of National Defence (DND) Polar Epsilon NRT (Near Real Time) ship detection project, several systems improvements have been made, particularly to order handling and mission planning. These improvements allow for the introduction of the two new Polar Epsilon reception stations, and facilitate downlink sharing between government reception stations. The Polar Epsilon changes have now all been rolled out into operations.

- Ordering Interfaces for HMA Project: Under the HMA project contract with ESA, MDA has been developing an infrastructure to support a standardized way of querying the catalog, reporting on data acquisition, and ordering data. In this context, a machine-to-machine interface for fulfilling these functions is being developed. Web services are being created from more traditional applications, such as a web application in the case of the OD (Order Desk) system, or a standalone tool in the case of the APT (Acquisition Planning Tool).

An APT web server has already been developed which currently supports a catalog query service as well as receiving acquisition coverage from the catalog. - An Order Desk web server is being developed with new web services such as creating an order, submitting an order, or obtaining status on an order element (Ref. 29).

• The RADARSAT-2 spacecraft and its payload are operating nominally in 2011.

• Status of mission imagery in August 2010: 31) 32)

- All impulse response measures have remained consistently with specification

- Radiometry has remained stable since start of Operational Phase. No overall system calibration adjustments have been made since the last CEOS meeting.

- Periodic polarimetric calibration adjustments keep the accuracy well within original goals

- The geolocation accuracy is currently assessed as < 10 m for all single beam modes.

- Additional Quad-Pol beams have been made available operationally. There are now 31 swath positions available, spanning 20º - 49º incidence.

2011: Introduction of five new observation modes for RADARSAT-2 SAR instrument: 33) 34) 35)

RADARSAT-2 is providing new and better opportunities for spaceborne monitoring of vessel traffic and fishing activities because of better flexibility in the choice of resolution, polarization and look direction. Due to user demand, five new modes were installed on the satellite in 2011. The new modes give the possibility to order images with better resolution and quad-polarisation (for some of the modes). This may be better for some scenarios in operational ship detection due to the increased swath width and coverage area for the new modes. Prior to the installation of the new modes, high resolution and quad-polarisation images only covered small areas. For ship detection these images have mainly been used for research purposes, harbor areas or over a known small area of interest.

The RADARSAT-2 SAR sensor is very flexible. It is possible to reprogram the sensor for example according to resolution and swath width. Five new modes have now been made due to user demand. The new modes open up new opportunities to use images with good resolution and relatively wide swath width at the same time. The Wide Fine Quad-Pol and Wide Standard Quad-Pol modes give the opportunity to choose quad-pol images with wider swath widths compared to the original modes.

Beam mode

Nominal swath width

Swath width for regular corresponding mode

Range resolution

Azimuth resolution

Incidence angle

Polarization (pol)

Applications

Wide ultra fine

50 km

20 km

1.6 - 3.3 m

2.8 m

30-50º

Single-pol

Same resolution as ultra fine mode, but wider swath

Wide multi-look fine

90 km

50 km

3.1-10.4 m

4.6-7.6 m

29 - 50º

HH,VV, HV, or VH

Wider swath than milti-look fine, butsame spatial and radiometric resolution. 50% overlap between individual swaths

Wide fine

120-170 km

50 km

5.2-15.2 m

7.7 m

20 - 45º

Single-pol or dual-pol

Good resolution (same as for fine beam) and a wider swath (same as for wide beam)

Wide fine Quad-Pol

50 km

25 km

5.2-17.3 m

7.6 m

18 - 42º

Quad-pol

21 beams. Wider swath width. Same spatial resolution as for the original modes. 50% overlap between the modes

Wide standard Quad-Pol

50 km

25 km

9-30.0 m

7.6 m

18 - 42º

Table 2: New additional beam modes of RADARSAT-2

Wide Fine mode: The Wide Fine modes are useful when both a finer spatial resolution (same as for the Fine Beams) and wider swath width (same as for the Wide Beams) are required. There are three Wide Fine Resolution Beams, F0W1 to F0W3, with swath widths of 170 km, 150 km and 120 km. They cover an incidence angle range of 20 to 45º. A nadir ambiguity may appear as a narrow bright line parallel to the flight direction for F0W3 images. One single-pol (HH, VV, HV or VH) image or two dual-pol images (HH+HV or VV+VH) can be acquired.

Wide Multi-Look Fine Mode: The Wide Multi-Look Fine Beam modes offer a wider coverage than the original Multi-Look Fine beam modes (90 km compared to 50 km), but have the same spatial and radiometric resolution. The nine Wide Multi-Look Fine Beam modes are able to cover the incidence angle range between 29-50º. There is more than 50 % overlap between the individual successive sub swaths. Only one single-pol image is available in this mode (HH, VV, HV or VH).

Wide Ultra-Fine Mode: The same spatial resolution as the Ultra-Fine Beam mode is obtained for the Wide Ultra-Fine Beam mode. These Beam modes aim at applications which require good resolution, but wider swath width (at least 50 km) as the regular Beam modes. The beams cover an incidence angle range of 30 -50º. Only one single-pol image is available in this mode (HH, VV, HV or VH).

Wide Standard Quad-Polarisation Mode: These 21 Wide Standard Quad-Polarisation Beam modes operate in the same way as the regular modes, but have a wider swath width of approximately 50 km and the same spatial resolution. The incidence angle range of 18-42º is covered with a 50 % overlap between the swaths.

Wide Fine Quad-Polarisation Mode: The Wide Fine Quad-Polarisation Beam modes have a wider swath width of about 50 km (compared to 25 km for the regular beams) and the same spatial resolution as for the original beams. There are 21 beams with overlaps of 50 % between the swaths, covering an incidence angle range between 18-42º.

Table 3: Description of the new beam modes (Ref. 33)

• The RADARSAT-2 spacecraft and its payload are operating nominally in 2010. Commercial spacecraft operations are conducted by Telesat (Ottawa) for CSA/MDA (the mission comprises a large system and a number of entities, organizations, and stakeholders inside and external to MDA.). 36) 37)

• In late April of 2010, RADARSAT-2 has successfully completed its second year of routine phase operations. The mission operations team has continued to operate and maintain the system to meet and exceed performance specifications. In particular, the system outage trend has decreased. In the last year orbital collision risk mitigation measures have become more important and RADARSAT-2’s first avoidance maneuver was successfully executed as a precaution. The team continues to implement system and operations improvements, including new and improved beam modes. A significant upgrade to support the DND Polar Epsilon project is underway. The system will continue to evolve to respond to customer and market needs. 38)

- In parallel with the commercial operations, RADARSAT-2 supported a series of MODEX (Moving Object Detection Experiments) conducted by Defence R&D Canada (DRDC), involving special SAR antenna configurations and beam/modes. The initial trials work is now largely complete.

- The RADARSAT-2 spacecraft has continued to meet performance specification with margin throughout the routine phase. There have been no unusual trends in spacecraft thermal or power performance. Battery performance in the annual eclipse season has been nominal with battery depth of discharge of less than 10% of the battery capacity (Ref. 38).

• In January 2010, MDA provided free imagery acquired by the RADARSAT-2 satellite over Haiti in support of disaster recovery and reconstruction efforts by the Canadian Government and relief agencies through the Canadian Space Agency's participation in the International Charter "Space and Major Disasters". 39)

• RADARSAT-2 is a contributing mission to GMES (Global Monitoring for Environment and Security) of the EU. In early 2010, MDA is completing a project to implement the HMA (Heterogeneous Mission Access) catalog interface capability -- to accomplish a coherent access to archives for the support of scientific exploitation. 40)

• Early during the routine phase, the new spotlight mode was added to the system. This provides a resolution of better than one meter in azimuth. 41) 42)

• In May of 2008, RADARSAT-2 polarimetric SAR test data for Natural Resources Canada became available.

RADARSAT-2 was declared operational on April 24, 2008 when the commissioning phase ended with the Commissioning Review. - Since that time, additional modes such as Spotlight and MODEX (i.e. GMTI) have been introduced, and work has been undertaken to optimize performance of all modes beyond the original specifications. 43) 44) 45) 46) 47)

• Left or right looking: Left- and right-looking modes are available on RADARSAT-2. This permits routine Antarctica mapping and, in emergency situations, the choice of beam mode and position can be set to ensure the greatest repeat coverage of the region of interest.

• In late March 2008, all the pre-defined modes of RADARSAT-2 had demonstrated performance that met requirements in all aspects of image quality. Initial radiometric, polarimetric and geolocation calibration had been completed for all modes.

• The very first images of RADARSAT-2 were acquired on Dec. 18, 2007 just four days after launch.

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Figure 7: The first Quad Pol image of RADARSAT-2 on Dec. 18, 2007 showing the region of the Sermilik Fjord in Greenland (image credit: MDA)

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Figure 8: RADARSAT-2 Quad Pol image of Devon Island in the Canadian Arctic Archipelago (image credit: MDA)

 


 

Sensor complement:

The payload module consists of the SAR instrument, the SAR antenna, and specific support equipment required to perform such functions as timing and control of the payload, signal distribution, signal detection, thermal control, data storage, and X-band downlink.

SAR (Synthetic Aperture Radar) instrument:

The SAR instrument specification is outlined in Tables 4 and 5 with the following functional capabilities: 48)

• Operationally, the SAR instrument is identical to that of RADARSAT-1 (with regard to mission control, mission planning, and data collection and processing)

• Fully integrated into the RADARSAT-1 ground segment

• Supports tandem mission operations with RADARSAT-1

• All RADARSAT-1 image quality specifications are met or exceeded

• A 3 m ultra-fine resolution is provided (improved object detection)

• A selectable incidence angle and the choice of left- and right-looking imaging capability is provided with the ability to maneuver the S/C on command. This feature offers much quicker revisit times for handling user requests. It also doubles FOR (Field of Regard) for event monitoring support applications.

Provision of fully polarimetric imaging modes. Polarimetry modes (amplitude and phase information) increase the information content of the measurement.

• An increased downlink power permits the use of 3 m antenna dishes for ground receiving stations

• The encrypted downlink science data stream maintains service confidentiality

• The utilization of onboard GPS receivers offers real-time position knowledge within 60 m

• The functional exploitation of solid-state recording technology permits the provision of new customer services (selection of image scenes and receiving station)

The most fundamental change in the instrument design from RADARSAT-1 is the introduction of an active phased array antenna on RADARSAT-2 providing two-dimensional beamforming and beamsteering to produce the many (over 200) beams required for the various imaging modes. This replaces the passive slotted waveguide antenna with one-dimensional elevation beamforming of the earlier S/C. The full set of modes is given in Table 5, and they are illustrated in Figure 9. All modes are available in both left- and right-looking satellite orientations. 49) 50)

The AIU (Antenna Interface Unit) and 16 CDU (Column Drive Units), one on each column, perform the command & control and the power distribution functions of the antenna.

Center Frequency

5.405 GHz, C-band (5.5 cm wavelength)

RF bandwidth

11.6, 17.3, 30, 50, or 100 MHz

Transmitter power (peak)

1650 W (normal mode), 2280 W (ultra fine mode)

SAR Antenna

- Aperture size: 15 m x 1.37 m
- Type: 2-D active phased array antenna
- The 512 T/R modules are organized as 32 rows of 16 TRMs per row
- All TRMs have independent control of transmit phase, and receiver phase and amplitude, for both vertical and horizontal polarizations.
- Transmitter and receiver phase and amplitude control in the elevation dimension allow for the formation and steering of all beams.
- Transmitter phase control in the azimuth dimension allows the formation of the wider beams required for the ultra-fine resolution mode.

Antenna polarization

- Full polarimetric (HH, VV, HV, VH)
- Simultaneous reception of two polarizations: H and V or LHC and RHC.
- Selectable transmission of one H, V, LHC or RHC polarization. Quad polarization beams allow dual transmit polarization and dual receive polarization.
- The polarization isolation is better than 25 dB (≥25 dB)

Deployment mechanism

Antenna, ESS (Extendible Support Structure)

Imaging mode delay time

10 ms

X-band downlink margin at 5º elevation

9 dB (allows 3 m receiving ground station antenna)

Data rate (max)

105 Mbit/s [recorded (encrypted) and realtime]

Mass of SAR antenna

750 kg

Table 4: SAR instrument parameters





RADARSAT-1/2 modes with selective polarization

Transmit H or V
Receive H or V or (H and V)

Beam modes

Nominal swath width

Incidence angles to left or right side

Nr. of looks Range x Azimuth

Spatial
resolution (m)

Swath coverage left or right (km)

Standard

100 km

20º - 49º

1x4

25 x 28

250-750

Wide

150 km

20º - 45º

1x4

25 x 28

250-650

Low incidence

170 km

10º - 23º

1x4

40 x 28

125-300

High incidence

70 km

50º - 60º

1x4

20 x 28

750-1000

Fine

50 km

37º - 49º

1x1

10 x 9

525-750

ScanSAR wide

500 km

20º - 49º

4x4

100x100

250-750

ScanSAR narrow

300 km

20º - 46º

2x2

50 x 50

300-720

New RADARSAT-2 modes (beyond those offered by RADARSAT-1)

Polarimetric: transmit H, V on alternate pulses
Receive H, V on any pulse

Standard Quad polarization

25 km

20º - 41º

1x4

25 x 28

250-600

Fine Quad polarization

25 km

20º - 41º

1x1

11 x 9

400-600

Selective single polarization
Transmit H or V
Receive H or V

Multi-look fine

50 km

30º - 50º

2x2

11 x 9

400-750

Ultra-fine

20 km

30º - 40º

1x1

3 x 3

400-550

Table 5: SAR imaging modes of RADARSAT-2

SAR instrument calibration: The design of the RADARSAT-2 payload has made it possible to operate in fully polarimetric quad-polarization (quad-pol) modes, which introduce the requirement for polarimetric calibration on top of the radiometric calibration of all other modes. In addition to these two primary forms of calibration, there are also a number of other forms of image measurement and payload characterization work which must be undertaken in order to ensure that the required image quality is achieved and maintained. An IQS (Image Quality Subsystem) has been established within the RADARSAT-2 ground segment to perform these tasks, and the key tools required for analysis of data and generation of calibration information have been built into a suite of software provided in several IQS workstations. 51) 52)

Radarsat2_AutoB

Figure 9: Some observation geometries and coverage modes of RADARSAT-2 (image credit: MDA)

SAR instrument overview:

The SAR payload consists of the SAR Antenna and the Sensor Electronics (SE) as shown in Figure 12. The Antenna includes a planar distributed phased array antenna having 512 subarrays each interfaced to one solid state transmit / receive (T/R) module. The long, or horizontal, dimension (15 m) of the array is directed along the direction of flight. The short, or vertical, dimension (1.4 m) is oriented such that the normal to the physical antenna aperture is inclined towards the Earth's surface at an angle of 29.8º with respect to the vertical between the spacecraft and the ground. 53) 54)

The subarrays are each provided with dual ports to enable transmission and reception in horizontal polarization (HP) mode (electric field vector aligned with long dimension of the array) and vertical polarization (VP) mode (electric field vector aligned with the short dimension of the array). The 512 T/R modules and their associated radiating subarrays are arranged in 16 columns uniformly spaced over the length of the array. Each column comprises 32 T/R modules and subarrays uniformly spaced over the height of the array.

Low level transmit signal generation and on-board receive signal handling is performed by the SE (Sensor Electronics) subsystem. Low power transmit signal pulses at C-band are generated by a waveform generator within the SE and distributed to each T/R module via a PAA (Power Amplifier Assembly) and a corporate signal distribution network comprising APDN (Azimuth Power Dividing Networks) and EPDN (Elevation Power Dividing Networks). Radar echo pulses are amplified by the T/R modules and collected by two independent sets of corporate combining networks, one for each polarization. The receive path combining networks have the same physical and electrical properties as the transmitting network, but operate in the reverse direction.

The output signals from each of the combining networks are routed via the SM (Switch Matrix) to the two receiver channel inputs of the SE. The SM controls the routing of received signals from the antenna wings to the SE input ports as required by the current imaging mode, and allows a low power reference sample of the transmitted pulse to be inputted to the SE during the transmit pulse time.

Radarsat2_AutoA

Figure 10: Line drawing of the RADARSAT-2 spacecraft (image credit: MDA)

The antenna radiating elements, T/R Modules, CDUs and associated power, control and RF signal interconnecting harnesses and distribution networks are mounted on the SAPA (SAR Antenna Panel Assembly) as shown in Figure

Radarsat2_Auto9

Figure 11: The SAPA layout (image credit: MDA)

Radarsat2_Auto8

Figure 12: Overview of the SAR instrument architecture (image credit: MDA)

T/R module architecture (Figure 13): The T/R module provides the transmit RF power amplification and receive signal amplification for the antenna array. A T/R module includes two transmit power amplification channels and two receive channels. The two receive channels may be operated simultaneously for reception of V and H polarized signals. One transmit channel can be selected depending on the setting of the RF switches. If required, the transmit operation can alternate between H and V on alternate pulses.

A nominal peak pulse power of +6 dBm is applied to the 50 ohm transmit input port of each T/R module. The center frequency is 5.405 GHz, and maximum bandwidth, dependent on operating mode, is 100 MHz. The T/R module sends the Transmit RF pulse by the HP or VP port to the subarray. Nominal peak pulse output power levels are +40 dBm (10 watts) in high power mode and +38 dBm (6.3 W) in low power mode, into 50 ohm. Only one transmitter pulse output can be active at any one time. The same ports provide HP and VP 50 ohm RF receive interfaces with the subarray.

A control board, containing digital ASIC and discrete devices, controls the operation of T/R module RF functions. Two identical ASIC's, one dedicated to each RF channel, provide serial interface control, modulator drive, timing and phase and amplitude data memory functions for their associated RF channel.

Radarsat2_Auto7

Figure 13: Block diagram of the T/R module configuration (image credit: MDA)

 

MODEX (Moving Object Detection Experiment):

MODEX represents an experimental GMTI (Ground Moving Target Indication) capability of the SAR system on RADARSAT-2. During MODEX operation, the SAR antenna is partitioned into two subapertures along the satellite track to sequentially observe the same scene from the same spatial point. The technique allows a wide variety of operating modes and parameters to be tried. In one version of the experiment, similar to ultra-fine mode, MODEX makes use of the dual-receive capability of the RADARSAT-2 antenna. This dual-receive capability provides two apertures aligned in the along-track direction, which is suitable for detecting moving objects. By processing the received echo data using along-track interferometric techniques and DPCA (Displaced Phase Center Antenna) techniques, objects with non-zero radial velocities can be detected and their radial velocities can be estimated. 55) 56) 57)

MODEX has been implemented through collaboration between DND, the Canadian Space Agency (CSA), and the satellite builder, MDA Corporation, Ltd. Three GMTI detection algorithms were implemented: 58)

• The first one is the classical DPCA (Displaced Phase Center Antenna), which is based on using two separate signal channels that observe the same scene at different times from the same point in space. The presence of moving targets is detected in the differential data by comparing the magnitude of the signal difference against a computed CFAR (Constant False Alarm Rate) threshold.

• The second detector is a new algorithm called the Hyperbolic detector, which is based on the combination of two independent metrics. The first metric is used to detect targets with a high probability of detection while allowing a rather large number of false alarms. A second metric is then applied to only the targets which exceeded the detection threshold of the first metric to reduce the false alarms while preserving the high probability of detection. The two independent metrics are combined into one two-dimensional metric. The resulting detection threshold from the combined metric is a hyperbolic curve instead of a classic CFAR threshold value.

• The third detection algorithm is called the HATI (Histogram Along-Track Interferometry) detector. This algorithm differs from the other detectors in that it uses an adaptive nonparametric CFAR detection scheme that does not involve the theoretical modeling of clutter statistics. Although the HATI algorithm uses ATI for moving target detection, the adaptive histogram techniques to calculate CFAR thresholds can also be applied to other detectors such as DPCA.

Radarsat2_Auto6

Figure 14: MODEX-1 processor architecture of the RADARSAT-2 mission (image credit: DRDC)

In addition to the dual-receive mode of operation, RADARSAT-2 also supports an alternating-transmit mode where pulses are transmitted alternately from each wing, and received alternately on each wing. This toggle mode allows greater separation of the two-way phase centers in the along-track direction. The transmitter toggling approach (between fore and aft sub-apertures) has the advantage of maintaining the same phase-center distance as the dual-channel case, which is 3.75 m for RADARSAT-2, and is capable of generating three phase centers.

Six sets of MODEX data were collected during RADARSAT-2 commissioning trials: three in the MODEX-1 mode and three in the MODEX-2 mode (or the toggle mode). Preliminary MODEX results showed that the sensor is capable of detecting and measuring both cross-track and along-track velocity components as low as 5 m/s. The accuracy of the measurements is about ±0.3 m/s in the cross-track direction and ±4.0 m/s in the along-track direction (Ref. 58).

Note: MODEX-1 represents the MODEX processor implementation at launch which includes a preprocessor to prepare the data for GMTI processing as well as two-antenna techniques to detect and estimate moving target parameters. MODEX-2 is a processor upgrade which includes toggle mode data processing and waveform diversity processing as well as three-antenna detectors and estimation methods.

The MODEX experiment is being funded by DND (Department of National Defense) of Canada for technology demonstration purposes. DND aims to develop a SAR-GMTI processing system to investigate the military and commercial utility of space-based moving target measurements. MODEX is being carried out by DRDC (Defense Research and Development Canada).

RADARSAT-2 data: RSI (RADARSAT International), a subsidiary of MDA, will market and distribute RADARSAT-2 data on a commercial basis. 59)

In addition, Canada is going to use the RADARSAT-2 data in the following programs:

SOAR (Science and Operational Applications Research for RADARSAT-2), a joint partnership program between the Canadian government and MDA through CSA and CCRS (Canada Center of Remote Sensing) of NRC (Natural Resource Canada).

- The SOAR program provides access to RADARSAT-2 data only for research and testing purposes.

- The SOAR program provides an opportunity to explore the enhanced capabilities of RADARSAT-2 and their potential contributions to applications through a loan of limited amounts of RADARSAT-2 data to research projects.

Now that the satellite is fully operational, the Government of Canada will develop specific R&D initiatives under the SOAR program umbrella.

Project Polar Epsilon: A surveillance and ship detection initiative within Canada's Defence Program. RADARSAT-2 wide-area data will be used to enable all-weather, day/night persistent surveillance of Canada's Arctic region and ocean approaches (Canada has the longest coastline in the world at 243,772 km and a corresponding marine area of responsibility of over 11 million km2). The goal in marine security is domain awareness: to know what is happening and where it is happening in the marine domain or ocean approaches to the borders.

Project Polar Epsilon invests in applications and ground segment infrastructure to receive and process RADARSAT 2 information. Polar Epsilon will deliver four main capabilities: near real-time ship detection; arctic land surveillance; environmental sensing; and maritime surveillance radar beam optimization. The near real-time ship detection capability will include local RADARSAT-2 satellite reception, processing and applications in support of the emerging Marine Security Operations Centers (MSOCs) on both of Canada's east and west coasts at or near Halifax and Esquimalt. 60) 61) 62) 63)

The RADARSAT-2 imagery analysis by the MSOCs will be complemented with optical imagery of the MODIS (Moderate-Resolution Imaging Spectroradiometer) instrument on various US missions. The provision of ocean color information from the MODIS sensors will assist the MSOCs with operational use of maritime patrol aircraft, ships, submarines and sonar performance prediction.

The RADARSAT-2 surveillance must be seen as complementary to future AIS (Automated Identification System) services onboard ships, mandated by the IMO (International Maritime Organization). AIS is a mixed ship and shore-based broadcast transponder system, operating in the VHF maritime band, which sends ship identification, position, heading, ship length, beam, type, draught and hazardous cargo information, to other ships as well as to shore. Of significance is that AIS can be monitored from satellites.

An AIS device will not be part of RADARSAT-2. RADARSAT-2 will only perform the ship detection function with its SAR imagery. However, Canada is planning to fuse commercial space-based AIS with coincidental RADARSAT-2 passes - this will help to confirm non-compliant AIS reports or no reports.

The follow-up system of RADARSAT-2, a three-spacecraft mission referred to as RCM (RADARSAT Constellation Mission), with launches in the timeframe 2012-14, is planning to combine SAR and AIS on the same spacecraft platform.

 


 

Ground segment:

The ground segment architecture is broken down into several subsystems as shown in Figure 15 (modular distributed system). Where possible, the existing RADARSAT-1 ground segment facilities and infrastructure are being reused. However, almost all software and computer hardware has been replaced by new systems. The use of up to date technology allows lower maintenance and operational cost while providing improved functionality. 64) 65) 66)

The RADARSAT-2 ground segment was upgraded from the RADARSAT-1 infrastructure and includes a Mission Control Facility at the CSA Headquarters at St. Hubert (near Montréal), Québec, and TT&C stations at St. Hubert and at Saskatoon, Saskatchewan. The CSA order desk will coordinate all government user requests for RADARSAT-2 data. MDA is responsible for the sale and distribution of RADARSAT-2 data to all commercial users. In May 2006, an MDA MOC (Mission Operations Center) was installed in St. Hubert.

Radarsat2_Auto5

Figure 15: Overview of RADARSAT-2 ground segment architecture (image credit: MDA)

Radarsat2_Auto4

Figure 16: Ground segment facility locations (image credit: MDA)

The RADARSAT-2 mission components are shown in Figure 17. In addition to internal and external system components and mission operations, the mission involves the data users, MDA business management, and the regulatory authority. The Canadian Government is a major mission stakeholder and receives data in return for its investment in the system development. RADARSAT-2 mission management concerns management of and/or interfacing with these components to ensure orderly conduct of the mission to meet mission objectives (Ref. 36).

RADARSAT-2 operations are characterized by intensive, highly automated, intermittent TT&C pass operations, supported by complex planning cycles to convert client orders into imaging and data downlink plans and to prepare on-board command schedules and upload command sequences. A multi-mission approach for operations provides cost and risk savings for participating missions.

Radarsat2_Auto3

Figure 17: RADARSAT-2 mission components (image credit: MDA)

RADARSAT-2 routine phase mission operations are functionally arranged as shown in Figure 18. These provide for the day-to-day end-to-end system operations and maintenance of the satellite and ground segment, including overall system and operations management, planning of satellite and ground reception activities in response to client orders, satellite command and control, and Canadian SAR data reception, archiving, cataloguing, processing and distribution. Operations development established plans for these functional areas.

Radarsat2_Auto2

Figure 18: RADARSAT-2 mission operations functions (image credit: MDA)

For a commercial mission, operations costs are an important metric. Early during development a cost model was established. This was updated throughout development so that cost metrics could be reviewed at design milestones and for comparison of operations approaches. MDA senior management took, and continue to take, a particular interest in reviewing the status and planning for mission operations costs in view of their impact on RADARSAT-2 business success. This led to frequent corporate reviews during development and to the setting of cost budget targets and goals which drove planning and implementation decisions (Ref. 36).

Regulatory environment: During RADARSAT-2 development a new regulatory environment was introduced in Canada governing commercial satellite remote sensing operations – the “Remote Sensing Space Systems Act”. This has had the effect that key mission and system requirements and plans, such as operational orbit parameters and control, performance of products generated from the SAR Payload, and the need to maintain and execute an end-of-life decommissioning plan, have become legal as well as mission responsibilities. An additional system activity reporting burden has also been imposed at mission level.

A system impact of this new regime concerned the changes needed to order handling to automate the otherwise operator intensive and potentially error-prone new “access control” rules for imagery imposed on clients by the regulations. A further mission management impact concerns the need for formal permission to enhance system capability in areas which improve licensed performance (Ref. 36).

In the spring of 2010, RADARSAT-2 is starting in its third year in orbit and in its third year routine phase operations. Despite the system complexity, commissioning was completed relatively smoothly. System and operations performance in the routine phase has met and surpassed system requirements. A maintenance policy was adopted early in development and its implementation has proved to be successful. The mission operations processes and system were adapted in response to a new regulatory environment introduced shortly before launch. A mission operations risk management process has been adopted and includes orbital collision avoidance measures. A number of operations and system enhancements have been implemented in parallel with continuing operations. The system and operations will continue to evolve to meet business needs (Ref. 36).

 

Polar Project Epsilon (first attempts):

Leveraging the programmability of the RADARSAT-2 sensor, MDA developed and assessed two new ScanSAR beam modes: a 450 km wide ship detection optimized beam mode in the HH polarization channel, and a 530 km wide multi-purpose beam mode in the HH and HV polarization channels. These new beam modes are significantly better, offering nearly uniform ship detection of much smaller vessels across the full swath width, when compared to the existing RADARSAT-2 ScanSAR beam modes. 67)

Approach: To aid in the development of improved SAR images, MDA first constructed a tool which takes as input the relevant characteristics of a proposed SAR beam mode and outputs a statistically probable Minimum Detectable Ship Length (MDSL) metric at a 90% confidence level. This tool makes use of an empirical relationship between ship length and RCS (Radar Cross Section).

The tool makes the simplifying assumption that the entire RCS of the vessel is contained within a single resolution cell. This is valid since our objective is to assess the detectability of small ships which do satisfy this assumption. The tool is likely to underestimate the length of larger ships in the case where the RCS is spread over several resolution cells. Due to the complexity associated with ship orientation and length-to-width ratio, no attempt has been made to model larger ships to a higher fidelity, and therefore caution must be used when interpreting the absolute value of the MDSL metric reported.

The tool simulates, in a statistical sense, vessel detection being performed by a Constant False Alarm Rate (CFAR) filter using a K distribution. Here, the simulation is set to allow a maximum of 2 false alarms per 3600 km along-track. While a plethora of notable ship detection algorithms are currently available, this simplified tool allows to make useful relative comparisons between the existing RADARSAT-2 beam modes and these new beam modes to guide the beam mode design.

Recognizing that maritime domain awareness applications are not solely about vessel detection, the project developed two classes of beam modes: those which are optimized for vessel detection performance at the expense of other maritime applications, and multi-purpose beam modes which provide improved vessel detection performance, relative to the traditional beam modes, while continuing to support other maritime applications.

• The vessel detection optimized beam mode is 450 km wide, comprised of seven sub-beams (in the HH polarization channel only) spanning incidence angles ranging from 34º to 57º, and which makes use of the “dual-receive aperture” capability of the RADARSAT-2 sensor. The high data rate associated with the 50 MHz pulse, the high PRFs (Pulse Repetition Frequencies) and the dual-receive necessitated compressing the data using 1-bit block adaptive quantization (BAQ) encoding ito achieve real-time imaging and downlinking.

• The multi-purpose beam mode is 530km wide, comprised of eight sub-beams (in the HH and HV polarization channels) spanning incidence angles ranging from 20º to 50º. The high PRFs and the applications-driven need for low noise and dual-polarization with a minimum of 2-bit BAQ encoding made it necessary to use the 17 MHz pulse in order to achieve real-time imaging and downlinking.

Figures 19 and 20 illustrate the 90% confidence level MDSL metric versus incidence angle for the case of wind at 8 m/s at an angle of 45º relative to the beam. These plots compare the ScanSAR Wide beam mode (red lines) with the new ship detection optimized and multi-purpose beam modes (blue lines). Since both of these new beam modes have only one look in the azimuth direction, there will be a two-dimensional variation in the SAR sensor noise, leading to a corresponding variation in the MDSL metric (each of the blue lines represents a different position in azimuth within a burst) that has been described as an “egg carton.”

Radarsat2_Auto1

Figure 19: Relative comparison of the MDSL metric for the 500 km wide ScanSAR wide (HH polarization) and the 450 km wide vessel detection optimized beam modes (image credit: MDA)

Radarsat2_Auto0

Figure 20: Relative comparison of the MDSL metric for the 500 km wide ScanSAR wide (HH polarization) and the 530 km wide multi-purpose beam modes (image credit: MDA)

Beam mode

Minimum Beam Mode Detectable Ship Length (MDSL) metric

8 m/s wind speed

14 m/s wind speed

New 450 km wide vessel detection

15-20 m

28-48 m

New 530 km wide multi-purpose

38-45 m

74-105 m

ScanSAR narrow (HH polarization)

25-95 m

51-190 m

ScanSAR wide (HH polarization)

29-358 m

61-639 m

Table 6: Relative comparison of the MDSL metric for the new and existing ScanSAR beam modes

The two newly designed ship-detection application-specific ScanSAR beam modes have demonstrated that both beam modes offer marked improvement over the existing ScanSAR beam modes in terms of ship detection performance. While more detailed analysis remains to be carried out, the multi-purpose beam mode has been shown to be capable of supporting other ocean surveillance applications such as ice analysis, oil and pollution monitoring, ocean wave analysis, and wind retrievals.


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13) Pierre D. Beaulne, Charles E. Livingstone, “Evaluation of RADARSAT-2 Yaw Steering for SMTI Applications,” Proceedings of EUSAR 2010, 8th European Conference on Synthetic Aperture Radar, June 7-10, 2010, Aachen, Germany

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29) A. Hillman, P. Rolland, M. Chabot, R. Périard, P. Ledantec, N. Martens, “RADARSAT-2 Mission Operations Status,” Proceedings of IGARSS (International Geoscience and Remote Sensing Symposium), Vancouver, Canada, July 24-29, 2011

30) Daniel De Lisle, “RADARSAT-2 Government of Canada Data Utilization,” Proceedings of IGARSS (International Geoscience and Remote Sensing Symposium), Vancouver, Canada, July 24-29, 2011

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32) A. Hillman, P. Rolland, R. Périard, T. Luscombe, M. Chabot, C. Chen, N. Martens, “RADARSAT-2 Continuing System Operations and Performance,” Proceedings of IGARSS (IEEE International Geoscience and Remote Sensing Symposium) 2010, Honolulu, HI, USA, July 25-30, 2010

33) Tonje Nanette Arnesen Hannevik, “RADARSAT-2 new modes,”FFI (Norwegian Defence Research Establishment), July 10, 2012, URL: http://www.ffi.no/no/Rapporter/12-01094.pdf

34) Bob Slade, “RADARSAT-2 Product Description,” MDA, RN-SP-52-1238, Issue ?: April 15, 2011, URL: http://gs.mdacorporation.com/includes/documents/RN-SP-52-1238%20RS-2%20Product%20Description%201-8_15APR2011.pdf

35) Marco van der Kooij, “Examples of InSAR and other land applications RADARSAT-2,” Remote Sensing – The Synergy of High Technologies, Moscow, Russia, April 25-27, 2012, URL: http://www.sovzondconference.ru/upload/medialibrary/cb1/cb18010512d05be407b24c02757ef2ed.pdf

36) Anthony Hillman, “RADARSAT-2 Mission Management – experience from commercial remote sensing flight operations,” Proceedings of the SpaceOps 2010 Conference, Huntsville, ALA, USA, April 25-30, 2010, paper: AIAA 2010-1950

37) Jeff Hurley, “Operational Review: RADARSAT-1 & -2,” SEASAR Workshop 2010, January 25-29, 2010, Frascati, Italy, URL: http://earth.eo.esa.int/workshops/seasar2010/8_Hurley.pdf

38) A. Hillman, P. Rolland, R. Périard, A. Luscombe, M. Chabot, C. Chen, N. Martens, “RADARSAT-2 continuing system operations and performance,” Proceedings of IGARSS (IEEE International Geoscience and Remote Sensing Symposium) 2010, Honolulu, HI, USA, July 25-30, 2010

39) “RADARSAT-2 images used to monitor Haitian disaster to assess and support rescue,” Jan. 29, 2010

40) Ahmed Mahmood, “RADARSAT-1, RADARSAT-2 and RCM,” GSCB ()Ground Segment Coordination Body) Workshop, June 18-19, 2009, ESA/ESRIN Frascati, Italy, URL: http://earth.esa.int/gscb/papers/3.3_Mahmood.pdf

41) A. Hillman, P. Rolland, R. Périard, A. Luscombe, M. Chabot, C. Chen, N. Martens, “RADARSAT-2 Initial System Operations and Performance,” Proceedings of IGARSS (IEEE International Geoscience and Remote Sensing Symposium) 2009, Cape Town, South Africa, July 12-17, 2009

42) Anthony Luscombe, “Image Quality and Calibration of RADARSAT-2,” Proceedings of IGARSS (IEEE International Geoscience and Remote Sensing Symposium) 2009, Cape Town, South Africa, July 12-17, 2009

43) Information provided by Daniel De Lisle of CSA, St. Hubert, Quebec, Canada

44) D. De Lisle, “RADARSAT-2 Program Update,” Proceedings of EUSAR 2008, 7th European Conference on Synthetic Aperture Radar, June 2-5, 2008, Friedrichshafen, Germany

45) A. A. Thompson, A. Luscombe, K. James, P. Fox, “RADARSAT-2 Mission Status: Capabilities Demonstrated and Image Quality Achieved,” Proceedings of EUSAR 2008, 7th European Conference on Synthetic Aperture Radar, June 2-5, 2008, Friedrichshafen, Germany

46) A. Luscombe, P. LeDantec, K. James, A. Thompson, P. Fox, “RADARSAT-2 SAR Imaging Performance and Calibration,” Proceedings of EUSAR 2008, 7th European Conference on Synthetic Aperture Radar, June 2-5, 2008, Friedrichshafen, Germany

47) Luc Brûlé, Jill Smyth, Daniel DeLisle, Michael Manore, Mario Lagrange, Jean-Marc Chouinard, “RADARSAT-2: Capabilities and Benefits for the Canadian Government,” Proceedings of the 59th IAC (International Astronautical Congress), Glasgow, Scotland, UK, Sept. 29 to Oct. 3, 2008, IAC-08.B1.5.11

48) G. C. Staples, J. Hornsby, “Turning the Scientifically Possible into the Operationally Practical: RADARSAT-2 Polarimetry Applications,” Proceedings of IGARSS 2002, Toronto, Canada, June 24-28, 2002

49) P. Arsenault, , C. Grenier, I. Barnard, A. Baylis, “RADARSAT-2 Antenna Measured Beam Pattern Performance and Comparison with Software Predictions,” Proceedings of EUSAR 2006, Dresden, Germany, May 16-18, 2006

50) C. Grenier, I. Barnard, P. Arsenault, “The RADARSAT-2 Synthetic Aperture Radar Phased Array Antenna Performance Analysis Methodology,” Proceedings of EUSAR 2004, Ulm, Germany, May 25-27, 2004

51) A. Luscombe, A. Thompson, K. James, P. Fox, “Calibration Techniques for the RADARSAT-2 SAR System,” Proceedings of EUSAR 2006, Dresden, Germany, May 16-18, 2006

52) R. Touzi, R.K. Hawkins, S. Côté, “Data Quality Assessment of Polarimetric Radarsat-2: Preliminary Results,” Proceedings of the 4th International POLinSAR 2009 Workshop, Jan. 26-30, 2009, ESA/ESRIN, Frascati, Italy, URL: http://earth.esa.int/workshops/polinsar2009/participants/265/pres_5_Touzi_265.pdf

53) A. Brand, C. Grenier, I. Barnard, “RADARSAT-2 T/R Module Development,” Proceedings of the 13th Canadian Astronautics Conference, ASTRO 2006, Montreal, QC, Canada, organized by CASI (Canadian Astronautics and Space Institute), April 25-27, 2006

54) S. Riendeau, C. Grenier, “RADARSAT-2 Antenna,” Proceedings of the 2007 IEEE Aerospace Conference, Big Sky, MT, March 3-10, 2007

55) S. Chiu, C. Gierull, “Multi-Channel Receiver Concepts for RADARSAT-2 Ground Moving Target Indication,” Proceedings of EUSAR 2006, Dresden, Germany, May 16-18, 2006

56) P. D. Beaulne, C. H. Gierull, C. E. Livinstone, I. C. Sikaneta, S. Chiu, S. Gong, M. Quinton, “Preliminary design of a SAR-GMTI processing system for RADARSAT-2 MODEX data,” Proceedings of IGARSS 2003, Toulouse, France, July 21-25, 2003

57) P. D. Beaulne, C. E. Livingstone, “An Experiment Plan to Test RADARSAT's-2 GMTI Capabilities,” Proceedings of EUSAR 2006, Dresden, Germany, May 16-18, 2006

58) Shen Chiu, Chuck Livingstone, Ishuwa Sikaneta, Christoph Gierull, Pete Beaulne, “RADARSAT-2 Moving Object Detection Experiment (MODEX),” Proceedings of IGARSS 2008 (IEEE International Geoscience & Remote Sensing Symposium), Boston, MA, USA, July 6-11, 2008

59) T. Luscombe, “RADARSAT-2: Early Results,” EOBN 2008 (Earth Observation Business Network), May 13-14, 2008, Richmond, BC, Canada

60) R. J. Quinn, “Transformation in Maritime Domain Awareness: Project Polar Epsilon and Automated Identification System,” Proceedings of the 13th Canadian Astronautics Conference, ASTRO 2006, Montreal, QC, Canada, organized by CASI (Canadian Astronautics and Space Institute), April 25-27, 2006

61) P. J. Butler, “Project Polar Epsilon: Joint Space-based Wide Area Surveillance and Support Capability,” Proceedings of IGARSS 2005, Seoul, Korea, July 25-29, 2005

62) J. Howes, “Polar Epsilon: Joint Space-Based Wide Area Surveillance and Support Capability,” EOBN 2008 (Earth Observation Business Network), May 13-14, 2008, Richmond, BC, Canada

63) P. J. Butler, “Project Polar Epsilon: Joint Space-Based Wide Area Surveillance and Support Capability,” Proceedings of IGARSS 2005, Seoul, Korea, July 25-29, 2005, Vol. 2, pp. 1194-1197

64) S. K. Srivastava, P. Rolland, “Meeting Global Customers Needs of RADARSAT-2 Data,” 58th IAC (International Astronautical Congress), International Space Expo, Hyderabad, India, Sept. 24-28, 2007, IAC-07-B1.4.04

65) P. Meisl, A. Bohane, “RADARSAT-2 Program,” Ground Segment Coordination Body Workshop, ESA/ESRIN, Frascati, Italy, June 19-20, 2007, URL: http://www.congrex.nl/07c24/papers/08_Meisl.pdf

66) P. Meisl, C. Pearce, D. Comi, “RADARSAT-2 ground segment,” Canadian Journal of Remote Sensing, Vol. 30, No 3, 2004, pp. 295-303

67) K. Beckett, A. Thompson, A. Luscombe, G. Stirling, “Optimization of RADARSAT-2 SAR Imagery for Vessel Detection Applications,” Proceedings of the SPIE Remote Sensing Conference, Toulouse, France, Vol. 7826, Sept. 20-23, 2010, paper: 7825-10, 'Remote Sensing of the Ocean, Sea Ice, and Large Water Regions 2010,' edited by Charles R. Bostater Jr., Stelios P. Mertikas, Xavier Neyt, Miguel Velez-Reyes, doi: 10.1117/12.865058


The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: ”Observation of the Earth and Its Environment: Survey of Missions and Sensors” (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates.