RCM (RADARSAT Constellation Mission)
The successor (and complementary) mission to RADARSAT-2 will be the RADARSAT Constellation Mission (RCM), consisting of three (small) spacecraft (with a potential to increase the number to six). RCM is an evolution of the RADARSAT program with improved operational use of SAR data and improved system reliability. The overall objective of RCM is to provide C-band SAR data continuity for the RADARSAT-2 users, as well as adding a new series of applications enabled through the constellation approach. The SAR imagery is required by various Canadian government users (including the Canadian Forces) at frequent revisit rates (high temporal resolution). RCM will primarily collect wide-area data with an average daily revisit of Canada and daily access to 95% of the world. The main uses of the RCM data are expected to be in the areas of: 1) 2) 3) 4) 5) 6) 7) 8) 9) 10) 11)
• Maritime surveillance/national security - which covers a broad range of potential applications areas, including ice and iceberg monitoring, marine winds, oil pollution monitoring and response, and ship detection.
• Resource management (e.g., disaster monitoring and ecosystem monitoring).
The primary areas of interest are the landmass of Canada and its surrounding Arctic, Pacific and Atlantic maritime areas (Canada has a coastline of 243,772 km in length, the longest of any country in the world). The images and derived information are required to be provided to Canadian government users at frequent area coverage rates.
Table 1: Comparing RCM and RADARSAT-2 revisit capabilities
Figure 1: RCM daily world access (image credit: CSA)
Figure 2: Three satellite average daily coverage of Canada (image credit: CSA)
Some areas of SAR data applications: (Ref. 2)
• Ice monitoring: The largest operational user of Canadian SAR data is the Canadian Ice Service (CIS). RADARSAT data has proven to be a very cost-effective way of monitoring ice conditions to assure safe maritime navigation in the ice covered waters of the Arctic, the Great Lakes and the east coast of Canada. The CIS charts the distribution of sea ice, lake ice, river ice and icebergs in the navigable ice-covered waters around North America. For sea ice, lake ice and river ice, the primary parameters of interest are ice concentration, stage of development and floe size. These parameters can be measured effectively with ScanSAR wide-swath data at a resolution of 100 m. RCM will also monitor the iceberg distribution in the North Atlantic and in Alaskan waters.
• Oil spills: Satellite SAR has proven to be an effective and efficient method of detecting and monitoring oil spills. Oil spills form films of various thicknesses on the ocean and sea surfaces which result in dark signatures called slicks on the SAR images. The frequent revisit capability of RCM will offer enhanced potential to support oil spill control and cleansing. Near real-time SAR data will be provided to meet Integrated Satellite Tracking of Pollution (ISTOP) program’s requirements for both effective oil and ship detection.
• Flooding: The main issue with flood monitoring is timing. Civil security needs a flood map every morning to use it. Also knowledge of the terrain and water level evolution and predicted precipitation would help to mitigate risk and to issue warning. - The CSA is supporting the initiation of pilot projects that address disaster management from an end-to-end approach from mitigation, warning, response to recovery. These pilots ensure that satellite data are integrated into existing and planned systems and are used with a view to maximize benefits.
• Wind storms: RCM will likely contribute to the Hurricane Watch program by providing daily global coverage of the storms from space. Its capability to image in VV will benefit the hurricane’s application because available wind retrieval models are best developed for this particular polarization.
• Earthquakes: RCM SAR data can provide high-resolution imagery of earthquake-prone areas, high-resolution topographic data, and a high-resolution map of co-seismic deformation generated by an earthquake as well as monitoring of infrastructure. RCM will be able to provide interferometric pair of data every four days in between the three satellites maintained on a very tight orbit on a 12 day orbital cycle.
In 2004, the Canadian government decided to continue its RADARSAT program beyond RADARSAT-2. However, in the next phase, a new approach is being employed which focuses on the use of low-cost small satellites flying in a constellation configuration. The overall objective is to ensure C-band data continuity beyond RADARSAT-2 and to provide SAR imagery for operational applications such as maritime surveillance (ship detection, sea ice cover mapping, coastal monitoring), disaster management, and environmental monitoring (oil spills, ocean winds and wave heights). In addition, the global land surface observation services for the SAR user community are to be continued to permit change detection monitoring of areas affected by geo-hazards, climate change related processes, and man-made activities. The current concept involves three satellites with an option of flying up to six spacecraft. The RADARSAT constellation is planned to be operational by 2016. 12) 13) 14) 15) 16) 17) 18) 19) 20)
In general, a constellation of SAR satellites can provide a larger coverage, increased revisits, and higher system reliability than is possible with a single spacecraft. Also, the constellation concept offers the capabilities of interferometric SAR (InSAR) observations. The project was accepted with three essential objectives:
1) Provide C-band data continuity to main Canadian Government users
2) Provide daily coverage of maritime approaches of Canada for ice, ship and oil spill detection
3) Meet a stringent cost cap. Taken together, these three objectives imposed several constraints on the payload.
The requirements of C-band data continuity imposed the central frequency of 5.405 GHz, a bandwidth of 100 MHz, a minimum NESZ (Noise Equivalent Sigma Zero) of -22 dB and total ambiguity level below -16.5 dB. The coverage requirements for ice, ship and oil slick detection required that the payload can provide a compromise mode with a resolution of 50 m and four looks. To provide the desired coverage of Canada's maritime areas requires that the system provides an imaging swath of about 1000 km. A constellation of three satellites, each having an imaging swath of 350 km was selected to provide the desired coverage.
Moreover, to provide a daily access of the globe, a requirement was set to provide an access swath of at least 500 km. An additional access swath of 100 km was also defined but the ambiguity requirements are not enforced over that area. To ease up the selection of imaging areas, a requirement was made to provide four 350-km imaging swaths over the 600 km accessible area.
The low-cost approach requires that the design of the SAR system is in terms of mass, power consumption, volume, and antenna size, in compliance with the constraints imposed by using a low-cost launch vehicle and a small spacecraft bus.
Table 2: Overview of key mission requirements (Ref. 11)
Project status: (Ref. 19)
• In March 2006, the Canadian Space Agency (CSA) awarded a contract to MDA (MacDonald, Dettwiler and Associates) of Richmond, BC, to carry out the conceptual design and mission definition (Phase A).
• The Phase A of the RADARSAT Constellation project was completed in 2007. During this phase, a conceptual design concept was completed based on the user requirements developed by a Canadian User and Science Team in consultation with an International User Team.
• A Phase B contract was awarded in November 2008 for a period of 16 months with a Preliminary Design review planned for January 2010. The System Requirements Review was held at the end of February 2009. The spacecraft concept was adopted and design decisions have been taken to allow preliminary design to proceed. The RCM completed its Phase B in February 2010 with the mission's preliminary design review (PDR).
• Phase C started in February 2010 and is expected to last 22 months. During this Phase, Payload, Bus and Ground Segment Critical Design reviews will be achieved and the final satellite design will be approved (Ref. 20).
• Three satellites will be manufactured consecutively in Phases D1, D2 and D3 and are planned to be launched in 2014, 2015 and 2016 respectively. - An alternative schedule suggests starting the manufacture of all three satellites at the same time in Phase D and launching them within the timeframe 2014 to 2016.
• In 2010, the project is already in the detailed design phase with as objective a Mission CDR in December 2011. The Canadian government has already announced the funding of the manufacturing phase which is planned to start in 2012 (Ref. 2).
• Parallel efforts are in progress to implement new ground stations on the east and west cost and in the Northern part of Canada for data reception to support comprehensive maritime surveillance and monitoring of Canadian territory. There is also a plan to implement a TT&C station at Alert (located at 82º latitude in the Canadian North) in order to control the satellites on all orbits (Ref. 2). 22)
The RCM bus is based on the standard Magellan MAC-200 bus of Bristol Aerospace, Winnipeg, Manitoba, a division of MAC (Magellan Aerospace Corporation), Ottawa. The MAC-200 platform is also referred to as the Canadian Smallsat Bus. The spacecraft is box-shaped with a single fixed deployable solar panel. The SAR antennas are stowed for launch and deployed on orbit. The bus structure contains all bus and payload electronic units, with the payload units mounted within the bus structure. In May 2009, Bristol Aerospace received a contract from MDA for the preliminary design upgrade of the MAC-200 bus. 23) 24) 25) 26)
Figure 4: Artist's rendition of the RCM imaging concept (image credit: MDA, CSA)
The spacecraft is 3-axis stabilized. The ADCS (Attitude Determination and Control Subsystem) uses 6 CSS (Coarse Sun Sensors), 2 magnetometers, and 2 star trackers for attitude sensing. Actuation is provided by 3 torque rods and 4 reaction wheels. Onboard position knowledge (10 m, 2σ) is provided by a GPS receiver, the velocity knowledge is 0.15 m/s (2σ) on-orbit before processing.
The C&DH (Command & Data Handling) subsystem consists of two C&DH units (one active, one cold spare). All flight software, including the ADCS, resides on a fully redundant, high performance subsystem designed to meet a range of mission requirements. A unit manager performs watchdog functions and can switch between the two units. The C&DH is a multi-card system using an industry standard cPCI backplane to allow expandability for a multi-mission capability. The C&DH controls all bus functions; in addition, the subsystem provides the capability to perform payload processing through the addition of payload-unique interface cards. High speed interfaces, implemented in FPGAs, facilitate bus unit and payload command and telemetry handling. The payload data is stored in mass memory. The C&DH subsystem is CCSDS-compliant and provides up to 4 Mbit/s telemetry to the ground station with optional Reed Solomon encoding.
The MAC-200 power subsystem is an unregulated (+28 V ± 6 VDC), PPT (Peak Power Tracking) subsystem that employs a Li-ion battery connected directly to the power bus. The power subsystem includes power monitoring and fault protection, with multiple levels of load shed function. An average power of 220 W is provided with a peak power of 1600 W.
Propulsion subsystem: The baseline design has a total of six 1 N thrusters, 2 on the -x face and 4 on the -z face (designated the 2X-4Z thruster configuration). A 50 liter nitrogen pressured fuel tank, containing 37 liter of hydrazine, is placed near the -z face of the spacecraft in a manner that fuel usage nominally causes a migration of the centre-of-mass in the +z direction.
RF communications: The TT&C data are transmitted in S-band (redundant NASA STDN compatible S-band transponders). The uplink is a CCSDS-compatible digital bit stream modulating a STDN subcarrier, with a bit rate of 4 kbit/s. The downlink is a CCSDS-compatible link using QPSK modulation and having variable bit rates up to 4 Mbit/s. The downlink includes optional Reed Solomon encoding to achieve bit error rates down to 1 x 10-9. Spacecraft tracking is supported through the coherent operation of the transponder. The bus supports a set of S-band omni-directional antennas oriented in such a manner to achieve 99% spherical coverage with a ground station.
The payload data are transmitted in X-band.
Table 3: Overview of some spacecraft parameters
Figure 5: Illustration of a deployed RCM spacecraft, AIS is not shown (image credit: MDA, CSA)
Figure 6: Functional block diagram of the MAC-200 bus (image credit: Magellan Aerospace) 27)
Table 4: System characteristics of the RADARSAT missions
Launch: The launch of the first RCM spacecraft is planned for the fall of 2016 on a Falcon 9 launch vehicle. The launch of the second and third RCM spacecraft is planned for late 2017.
Orbit: Sun-synchronous circular orbit (dawn-dusk mission), altitude = 600 km, inclination = 97.7º, period = 97 minutes. The three spacecraft will be spaced at equal distances on the same orbital plane with a repeat cycle of 179 orbits/12days. The orbit selection allows revisiting the same area for coherent change detection every four days, which should enable a whole suite of interferometric applications.
The satellites will be equally spaced in the same orbital plane, following each other with a time separation of ~32 minutes. While the ground track of each satellite is slightly shifted due to the Earth rotation, this orbital configuration provides the required ground coverage over the Canadian maritime zones using the medium resolution ScanSAR mode.
Figure 7: Orbital configuration of the three-satellite constellation (image credit: CSA)
Table 5: Comparison of orbit parameters of the RADARSAT missions
Table 6: Evolution of the RADARSAT series (Ref. 11)
Sensor complement: (SAR instrument, AIS)
The technologies selected for the RCM antenna are derived from RADARSAT-2. The SAR antenna is a C-band, active phased array antenna that employs transmit and receive (T/R) modules, distributed across the antenna aperture. The baseline antenna concept provides a 9.45 m2 aperture but the aspect ratio varies between the two spacecraft concepts. The four-panel spacecraft concept consists of a 9.15 m x 1.03 m SAR antenna. The two-panel spacecraft concept consists of a 6.88 m x 1.375 m SAR antenna. The antenna mechanical interface to the bus is through HRMs (Hold Down and Release Mechanisms) when stowed and by an ESS (Extendable Support Structure) or support struts when deployed. Once deployed, the SAR antenna is required to point 37.5º off-nadir towards the dark side of the Earth. 28) 29)
In addition to the SAR antenna, the RCM payload consists of several bus-mounted units including the Central Electronics (2), SSR (Solid State Recorder), the X-band transmitter (2) and the X-band antenna (1).
The SAR payload mass (including antenna, support structure and bus-mounted components) is approximately 600 kg. The peak power consumption is approximately 1270 W and the orbit average power consumption is approximately 200 W.
Table 7: Key system parameters of the RCM
A variety of polarization capabilities are being implemented. In all imaging modes, the system can operate with single or dual polarization. With single polarization, the transmit and receive polarizations are individually selectable. In dual-polarization mode, the transmit polarization is one of H or V, and the receive polarizations are both H and V. A variation on dual-polarization is the compact polarization capability (Ref. 30).
In addition, two multi-polarization capabilities are provided.
- First, alternating polarization is available. It provides dual HH-VV polarization by operating in a burst mode, alternating HH and VV between bursts.
- Secondly, a quad-pol mode is provided. In this mode, the PRF is doubled compared to other modes, and H and V polarization are transmitted on alternate pulses. For each pulse transmitted, both H and V polarization are received. Thus the full scattering matrix is obtained.
Compact polarimetry: The objective of compact polarimetry is use a dual-polarization imaging mode to realize many (but not all) of the benefits of a quad-polarization mode without the severely reduced swath of quad-pol. The type of compact polarimetry supported by RCM involves the transmission of circular polarization, and dual reception of H and V polarization.
On RCM, compact polarimetry is achieved by a small modification to the T/R module design. The T/R modules were originally designed to transmit H or V polarization using separate transmit chains. The modification allows transmission on both chains simultaneously, thereby enabling the transmission of circular polarization (since circular polarization can be achieved by simultaneous H and V, but with a 90º phase shift between the H and V).
Doppler grid: The purpose of the Doppler grid capability is to support ocean current and marine wind applications by provision of a grid of Doppler centroid estimates in the product meta-data. These Doppler estimates will be provided on a 2 km x 2 km grid. By comparing the localized Doppler estimates to the overall Doppler estimates, an estimate of the component of the localized Doppler estimates due to ocean currents can be estimated. From such ocean current estimates, information about marine winds can also be deduced (Ref. 30).
Figure 8: Generic block diagram of the payload (image credit: MDA)
Figure 9: Characteristics of the RCM ScanSAR (left) and Stripmap (right) beam modes (image credit: CSA)
The system is designed as a medium resolution mission primarily dedicated to regular monitoring of broad geographic areas. This provides a 'big picture' overview of Canada's land mass and proximate water areas. Combined with higher resolution imagery from foreign missions going forward in the same time-frame, the data are expected to dramatically enhance Canada's ability to manage resources and the environment and to improve security by providing an operational surveillance system.
RCM will offer interferometric data on a four day repeat interval. This feature will add benefits to a range of applications like earthquake, volcano, landslides and permafrost conditions monitoring. In support of ecosystem monitoring, RCM will assure support to sustained development of agriculture and forestry resources, contribute to protection of the global environment and enhance understanding of climate change and its impact on ecosystems. SAR satellite images will enable the detection of changes over time in Canada’s coastal, wetlands and wildlife habitats.
Table 8: Imaging modes of RCM (Ref. 11)
Figure 10: Illustration of the RCM imaging modes (image credit: CSA, Ref. 11)
Operational imaging modes: The operational modes range from wide area surveillance with 500 km imaging swaths, to spotlight modes with resolution of 1 m in azimuth, and 3 m in range, as well as a large number of modes in between these extremes. The high resolution modes at 3 m and 5 m are primarily designed for disaster management. 30) 31)
- General-purpose wide-area surveillance: For wide area surveillance, and in particular, maritime surveillance, the need is for moderate resolution, while providing adequate sensitivity, a reasonable number of looks, and as wide a swath as possible with the given antenna aperture. With these objectives in mind, the Medium Resolution 50 m mode was designed. It is an 8-beam ScanSAR mode with approximately 50 m resolution in range and azimuth, NESZ of > -22 dB, 4 looks, and a 350 km imaging swath. It is comparable to the RADARSAT-1/2 ScanSAR narrow modes.
- Ship detection mode: To optimize ship detection performance, the fundamental need is to maximize the ship signal to “background noise” ratio. Here “background noise” is used to include two quite separate components: sea clutter and thermal noise. To maximize this ratio, separate strategies are available to separately maximize the ship signal, minimize sea clutter, and minimize noise.
One way to maximize ship signal level is to image with cell size resolution comparable to the size of ship to be detected, as clearly coarser resolution leads to lower signal level in a σο image, and finer resolution eventually leads to the ship RCS (Radar Cross Section) being spread over multiple pixels. Strategies to minimize the sea clutter level include imaging at high incidence where sea clutter is lower, and using cross-pol imaging which is known to have lower sea clutter level than co-pol imaging, at least at lower incidence. The main strategy to minimize noise is to use lower bandwidth imaging modes, as lower bandwidth means reduced noise.
- CCD (Coherent Change Detection): RCM is a constellation of three satellites, all in the same orbit plane, and all equally spaced around the orbit plane. Since the ground track repeat for each satellite is 12 days, there is a constellation CCD period of 4 days. To provide good CCD performance, a requirement for two dimensional bandwidth overlap of 75% has been imposed. This 75% bandwidth overlap requirement is prior to common band filtering and applies for slopes of up to 10% and over a range of incidence angles sufficient to give global access.
From the bandwidth overlap requirement, requirements for orbit maintenance and attitude control are derived. To maintain bandwidth overlap in range, the satellites must fly in a common orbit tube of radius on the order of 100 m. To maintain Doppler bandwidth overlap, very stringent attitude control in pitch and yaw is needed.
One of the biggest drivers for maintaining the orbit tube requirement is the orbit maintenance maneuver frequency. With a frequency of at most one maneuver per day, simulation and analysis have separately shown that the satellite can be maintained in the required tube (within 100 m radius for 99% of the time). Figure 11 shows the tube flying simulation result with daily maneuvers.
Figure 11: Tube flying error with daily orbit maneuvers (image credit: MDA)
The three-satellite configuration will provide complete coverage of Canada's land and oceans offering an average daily revisit at 50 m resolution, as well as a significant coverage of international areas for Canadian and international users. It will also offer average daily access to 95% of the world. The satellites will be interoperable, enabling tasking from one satellite to the next and will be equally spaced in a 600 km low earth orbit. The constellation has a flexible design, allowing up to six satellites to fly in the same plane.
The core data processing module in payload systems is often referred to as the CE (Central Electronics) subsystem. COM DEV Ltd. is the subcontractor to MDA for the CE. The main tasks of a CE subsystem are: demodulation, filtering and digitization of the SAR echo signals in the receive path, and generation of a Radar chirp, IF processing and RF power amplification in the transmit path. A simplified block diagram of the CE subsystem for the RCM payload is shown in Figure 12.
Figure 12: Simplified block diagram of the CE subsystem of RCM (image credit: COM DEV)
The CE poses many challenges in the analog, i.e., RF (Radio Frequency) domain. One of the challenges for the previous versions of the CE for RADARSAT-I and -II was in providing appropriate filtering for the multiple RBWs (Resolution Bandwidths). The present version of CE has to cater to 16 discrete RBWs ranging from 14 MHz to 100 MHz. The present design avoids the cumbersome SAW filter banks of previous versions by moving the RBW filtering to the digital domain. But the analog domain still is left with the serious challenge of meeting stringent system requirements on gain stability, noise figure, dynamic range, pulse distortion and spurious rejection – to name a few.
The receiver front end, shown in Figure 2, consists essentially of a switch to select between the transmit replica and the echo, a noise bandwidth limiting filter, the LNA, an image rejection filter that reduces the aliased thermal noise ratio (ATNR), and finally the mixer for down-converting the RF to the “baseband” IF which undergoes IF processing involving amplification and filtering before being digitized by the ADC (Analog Digital Converter).
Figure 13: Simplified block diagram of the receive front end of CE subsystem (image credit: COM DEV)
Receive DSP architecture: The CE receiver is an oversampling system where the analog signals are sampled at a higher rate and then down-sampled in the digital domain to a lower rate based on the RBW. The oversampling helps increase the signal-to-quantization noise ratio (SQNR) by 3 dB for every down-sampling by a factor of 2. However, down-sampling requires careful design of anti-aliasing digital filters.
A functional block diagram of the CE receiver DSP module is shown in Figure 14. The received echo or the replica signal at IF goes through a high speed ADC. As a first step in the receiver chain, the ADC output is digitally down converted (demodulated) to baseband. The use of Fs/4 demodulation (Fs = sampling frequency), simplifies the down conversion operation to sign alteration of the ADC sample stream without any need for complex multiplication. The resulting I and Q baseband demodulated streams are passed through anti-aliasing low pass filter (LPF) followed by M:1 down-sampler. The LPF and down-sampler constitute a decimator that reduces the sampling rate of oversampled analog signal.
Figure 14: Top-level view of the CE receive DSP module (image credit: COM DEV)
The design of the down-sampler and digital anti-aliasing filter is directed by two important criteria:
- The oversampling ratio, defined as the ratio between the actual sample rate and the Nyquist rate, should be optimized for all RBWs. The down-sampling ratio (M) of the CE receiver is carefully selected for different RBWs such that the oversampling ratio does not exceed 123 %.
- The number of taps in the resulting filters should not be too large for high decimation rates. This is generally achieved by two stage decimation where filter complexity in each stage is appropriate for the CE hardware.
Transmit DSP architecture: The basic requirement of the RCM CE transmitter is to provide high quality chirp waveforms at moderate power level suitable for distribution and amplification by the antenna T/R modules. Many of the quality aspects of the chirp waveform are related to the in-band chirp characteristics, timing, amplitude and phase, SNR, and out-of-band performance. Optimum RCM radar performance is achieved by using chirp waveforms that are not necessarily ideal up or down chirps with constant frequency slope and amplitude, but waveforms that may additionally embed some form of pre-distortion to correct for frequency-dependent distortions within the CE and/or the RCM radar payload.
IF sampling at the DAC puts a significant burden on storage and memory bus bandwidth requirements. As an alternative, the waveform samples can be generated at a lower rate that also meets the Nyquist requirements and eases the storage and memory bus bandwidth requirements. These samples can then be up-sampled and interpolated using low complexity digital filters before they can be fed to a DAC.
The basic functions of the Tx DSP module are waveform storage, high speed selection of waveform based on serial command, high speed memory retrieval of stored waveform selected, real time filtering, up-sampling and interpolating of the waveform to meet the DAC sampling rate requirement. A top-level view of the DSP subsystem within the CE transmitter is shown in Figure 15. The transmit pulse is generated digitally at baseband in the form of complex samples or I-Q pairs. Different from the CE receiver, the use of fixed sampling rate irrespective of the chirp RBW leads to a simpler design of the digital interpolation filter. The waveform samples are generated offline and stored in a flash on the DSP board that is capable of storing multiple chirp waveforms. Depending on the command from the ground station, one of the chirp waveforms is loaded into the SRAM from the flash.
Figure 15: Top-level view of the CE transmit DSP module (image credit: COM DEV)
Table 9: Comparison of SAR characteristics of the RADARSAT missions 33)
AIS (Automatic Identification System):
AIS is a payload of CSA and DND (Department of National Defense), Canada. The overall objective is to monitor the ship traffic in the extensive waters of Canada (wide area surveillance capability). 34) 35)
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.
• Swath coverage of AIS: 800 km
• Accuracy of AIS: Better than 90% ship detection, for class A ships, when ships are in view for a minimum of 5 minutes.
• Waveband: VHF (162 MHz)
• AIS Antennas: two orthogonal monopole pairs mounted on the SAR panel
- Provides omni-directional coverage (horizon to horizon)
- Provides circular polarization for receiving linearly polarized transmit signals that may have experienced Faraday rotation while propagating through the atmosphere
• AIS Receiver: Filters, amplifies, frequency down converts and digitizes the AIS signals
• AIS Processor (ground based): Performs data demodulation, signal de-collision and message extraction.
Figure 16: RCM AIS design concept (image credit: MDA)
Table 10: AIS data increase variants in support of global coverage
Figure 17: RCM deployed configuration (image credit: MDA) 36)
Figure 18: Maritime surveillance requirements of DND (image credit: CSA)
• The ground segment is driven by requirements for fast delivery of images acquired over Canada, and for fast tasking over international areas.
• It will be based on upgrades to the existing RADARSAT-1 and RADARSAT-2 Ground Segment facilities to allow basic constellation operations.
• The West and East Polar Epsilon stations will be used to support near real-time Maritime Surveillance
• Foreign stations, such as Svalbard, will be used for latency or data volume requirements.
The RCM ground segment is based on upgrades to the existing RADARSAT-2 ground segment, using the Gatineau and Prince Albert stations for data reception, the St-Hubert and Saskatoon stations for TT&C and the Svalbard station as a backup for TT&C and data reception. It will be harmonized for data reception at the Polar Epsilon coastal stations in order to support near-real time maritime surveillance. It will also include a fast tasking capability allowing access to the satellites on every orbit, likely achieved through international partnerships.
Figure 19: RCM baseline data reception stations (image credit: CSA, Ref. 26)
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