Attachment Sched S Tech Report.

This document pretains to SES-LIC-20160218-00154 for License on a Satellite Earth Station filing.

IBFS_SESLIC2016021800154_1129591

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS 1. ITU Registration Information for the exactView-1 Satellite The exactView-1 Satellite (EV1, formerly known as ADS-1B) has been registered with the ITU as part of the ADS satellite network and its frequency assignments have been recorded in the Master International Frequency Register: 1|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS 2. FCC Licensee Database: Search Results for 5150–5250 MHz in Alaska A February 16, 2016 search of the FCC’s General Menu Reports system for currently licensed operations in the state of Alaska in the 5150–5250 MHz band reveals only three operations, all by GUSA Licensee, LLC (affiliate of Globalstar Licensee, LLC): 2|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS 3. Coordination with Globalstar exactEarth coordinated operations for the ADS satellite network, of which exactView-1 is a part, with Globalstar Licensee, LLC, as confirmed by the email below: 3|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS 4. Additional Technical Information for the exactView-1 Satellite ExactView-1 ExactView-1 (formerly known as ADS-1B) was launched from Baikonur in Kazakhstan on July 22, 2012. It’s NORAD ID is 38709 and is registered by Canada with the ITU under the name ADS. EV1 is the highest detection performance Automatic Identification System (AIS) satellite ever built and utilizes high-speed C-band downlinks to frequently downlink mission data to ground stations in Svalbard, Norway. TT&C operations are performed from Guildford, UK. EV1 was built under contract for exactEarth by SSTL with COM DEV Europe (UK) supplying the advanced AIS transceiver payload system for this mission. Table 1 lists EV1’s key spacecraft characteristics and Figure 1 shows an image of the satellite. Figure 1 – The EV1 satellite Table 1: EV1 Key Spacecraft Characteristics Parameter Value Volume 600 x 600 x 620 mm Mass 87.7 kg Communication Mission Data 40 Mbps C-Band Downlink Attitude Control Nadir pointing, 3-axis stabilized using reaction wheels and magnetic torque rods DC Power ~ 65 W orbital average at BOL 4|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS Propulsion Cold gas EV1 Orbit EV1’s orbit is sun-synchronous with an altitude of approximately 817 km and an inclination of 99 degrees. Due to its high inclination, the spacecraft has global coverage multiple times a day. Figure 2 shows EV1’s high inclination orbit. Figure 2. High Inclination Orbit of EV1 Alaska Ground Station Coverage and Access with EV1 A ground station situated in Fairbanks has access to EV1 roughly 10 times a day. The mean pass duration is approximately 11.5 minutes. Figure 3 shows a typical Alaska – EV1 access pattern for a day. It can be seen that there is a single maximum access gap of almost 7 hours and this happens earlier in the day. Figure 3. EV1 – Alaska access pattern 5|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS Figure 4 shows the Az-El tracks of all passes of EV1 over Alaska plotted for one full week. It shows the satellite never passes over certain azimuths due to the inclination not being exactly 90 degrees. Figure 4. AZ-El access polar plot The coverage extent of the Alaska station, assuming a minimum display elevation mask of 3 deg is shown in Figure 5. Figure 5. Coverage extent of the Alaska station 6|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS Downlink RF Specifications EV1 uses an offset QPSK modulation scheme downlink with a fixed data rate of 40 Mb/s, 20 Mb/s uncoded. The transmitter RF power level is 2.95 W (4.97 dBW), with a maximum radiated EIRP of 8.7 dBW. The emission designator is 31M0G7DCT with 98% of the energy within a bandwidth of 31 MHz. The centre frequency of 5.183 GHz and is RHCP. The antenna design is based on a quadrafiler helix dimensioned and installed in such a manner such as to provide a quasi-isoflux radiation pattern (nadir/boresight referenced). The peak gain of the antenna is approximately 4 dBi at approximately at the Earth horizon (limb) as shown in Figure 6. Power Flux Density (PDF) on Earth The Flux density is calculated as: 𝐸𝐼𝑅𝑃 𝐹𝑙𝑒π‘₯ 𝐷𝑒𝑛𝑠𝑖𝑑𝑦 = 4πœ‹ × π‘‘ 2 Where: d is the distance from spacecraft to the point on the ground. EIRP is the Effective Isotropic Radiated Power of the Spacecraft. The EIRP of the satellite changes with the antenna pattern due to a variable amount of gain that is radiated at different off-boresight angles. Pattern is symmetrical in the phi angular dimension. The antenna beam pattern can be seen in Figure 6 below. The satellite boresight is always oriented to the nadir direction immediately below the satellite, using the EV1 three-axis ADCS system. 60 deg 30 deg Gmax=4d Bi -12 -9 -6 -3 0 dBi Figure 6. Transmit antenna gain pattern 7|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS By combining the antenna pattern with the change in distance as the satellite traverses a pass, the PFD versus elevation angle can be found in Figure 7. The red line shows the ITU PFD limit which must be respected. The predicted ground elevation angle versus PFD, in Figure 7, shows more than 1dB margin at the worst-case elevation angle of about 35 degrees. Figure 7. PFD vs. Elevation Angle Table 2 below shows the PFD margin over elevation angles shown in Figure 7. Table 2: PFD vs. Elevation Angle Parameters Units Nadir GES Rx entenna Degrees 90.0 80.0 70.0 60.0 50.0 40.0 30.0 20.0 15.0 10.0 5.0 elevation angle PFD in 4 kHz dBW/m2/4kHz -169.4 -169.3 -169.2 -168.2 -166.6 -165.4 -165.1 -166.6 -167.5 -169.1 -170.5 PFD limit per ITU dBW/m2/4kHz -164 -164 -164 -164 -164 -164 -164 -164 -164 -164 -164 5.447B Margin (if antenna dB 5.4 5.3 5.2 4.2 2.6 1.4 1.1 2.6 3.5 5.1 6.5 gain pattern is exact) The C-band PFD observed at the Alaska station for a single day is shown in Figure 8. The y-axis shows the PFD value and the x-axis is time in minutes during each satellite pass. The different colour curves represent the evolution of PFD level at the station for each of the different passes. For graphical clarity, 8|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS the centre point of each pass has been centred (note – lower elevation passes are shorter in duration and higher elevation passes are longer). This graph shows that a majority of the passes over the location do not reach the maximum PFD level and even those passes that do reach this peak level have significantly lower PFD for majority of the rest of the pass. Further insights into the likelihood of PFD levels over time are shown in Figure 9 in a 30-day simulation of all passes over the Alaska station. The 30-day simulation does not exhibit a higher level than the peak seen in a single day analysis (-165 dBm, below the maximum allowable PFD limit). Figure 8: PFD levels for all EV1 satellite passes over Fairbanks Alaska – January 26, 2016 Figure 9: PFD levels for all EV1 satellite passes over Fairbanks Alaska – January 1 to 26, 2016 9|Page

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS 5. Additional Technical Illustrations 10 | P a g e

Exhibit B – Technical Supplement FCC Form 312 Kongsberg Satellite Services AS 11 | P a g e


Document Created: 2016-03-09 10:50:24
Document Modified: 2016-03-09 10:50:24
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