Redacted Technical Annex

0353-EX-CN-2018 Text Documents

PointView Tech LLC

2018-04-26ELS_208690

REDACTED FOR PUBLIC INSPECTION ATHENA NGSO SATELLITE EXHIBIT 1 Technical Information to Supplement Form 442 and Application Narrative A.1 Scope and Purpose This exhibit supplements FCC Form 442 and contains the technical information referenced in the application narrative that is required by Parts 5 and 25 of the Commission’s rules. A.2 Radio Frequency Plan (§25.114(c)(4)) The Athena satellite will have two E-band uplinks and two E-band downlinks. The downlink emissions are nominally centered at 72 GHz and 75 GHz and the uplink emissions are nominally centered at 82 GHz and 85 GHz1. The bandwidth for both the uplinks and downlinks is 2.1852 GHz. The TT&C uplink will be conducted at 2082 MHz with an occupied bandwidth of 1.5 MHz. The TT&C downlink will be conducted at 8496.25 MHz with an occupied bandwidth of 2.3 MHz. Table A.2-1 shows the frequency ranges to be used by the Athena satellite. 1 There is the possibility that mild tuning may be performed from the planned 72, 75, 82 and 85 GHz centered carriers (e.g., 74.8 and 82.2 GHz may be used for example to mitigate any potential, mild “inter-channel interference” due to spectral regrowth issues and limited transmit- to-receive isolation). In addition, a limited number of tests, estimated at one to two dozen, may be performed with continuous wave (CW), unmodulated carriers as far out as the band edges (i.e., 71-76 GHz and 81-82 GHz) to measure the atmospheric attenuation characteristics. Any mild tuning or atmospheric measurement testing would maintain compliance with NTIA Redbook requirements for the licensed carriers. 1

REDACTED FOR PUBLIC INSPECTION Table A.2-1: Frequency Bands Used by the Athena non-GSO Satellite Type of Link and Transmission Direction Frequency Ranges 80.9074 – 83.0926 GHz E-band Uplink 83.9074 – 86.0926 GHz 70.9074 – 73.0926 GHz E-band Downlink 73.9074 – 76.0926 GHz TT&C Uplink 2081.25 – 2082.75 MHz TT&C Downlink 8494.75 – 8497.75 MHz The E-band uplink and E-band downlink will use both right-hand circular polarization and left- hand circular polarization. The TT&C uplink and TT&C downlink will use right-hand circular polarization. A.3 Non-GSO Orbital Characteristics (§25.114(c)(6)) The Athena experiment will consist of one non-GSO satellite operating in a circular sun- synchronous orbit at an altitude of 500 to 550 km. Table A.3-1 gives the other relevant orbital parameters for the Athena satellite. 2

REDACTED FOR PUBLIC INSPECTION Table A.3-1: Athena Satellite Characteristics Number of Orbital Planes 1 Satellites Per Orbital Plane 1 97.4° for 500 km case Inclination of the Orbital Plane 97.6° for 550 km case 5677 seconds (1 hour, 34.6 minutes) for 500 km case Orbital Period 5730 seconds (1 hour, 35.5 minutes) for 550 km case Apogee 500 – 550 km Perigee 500 – 550 km When visible to the earth stations at Active Service Arc minimum elevation angles of 5° - 30° (See Section A.4 for further explanation) Local Time of Descending Node 10:30 AM It is noted that additional orbital parameters, such as the argument of perigee and the initial phase angle of the satellite, are not applicable to a one-satellite non-GSO system in a circular orbit. The right ascension of the ascending node (RAAN) is dependent upon the specific launch date. The RAAN will change by 0.9856° per day in order to keep up with the 360° Earth rotation around the sun in 365.25 days. A.4 Frequency Bands and Coverage Areas (§25.114(c)(7)) As stated in Section A.2, the E-band downlinks will be in the 70.9074-76.0926 GHz frequency ranges and the E-band uplinks will be in the 80.9074-86.0926 GHz frequency ranges. During nominal operations, the satellite will only transmit and receive in the E-band when it is at an elevation angle greater than or equal to 30° from one of the earth stations located in the Los Angeles/Ventura county area. However, there may be some experiments in which the satellite will transmit and receive in the E-band when it is at a minimum elevation angle of 10°. TT&C will be performed in the 2081.25-2082.75 MHz frequency band for the uplink and the 8494.75-8497.75 MHz band for the downlink. For TT&C, the satellite will only transmit and receive when it is at an elevation angle greater than or equal to 5° from the Mojave, Brewster and 3

REDACTED FOR PUBLIC INSPECTION Albuquerque earth stations. Figures A.4-1 and A.4-2 show the coverage areas for the TT&C links based on these minimum elevation angles. The spacecraft will only transmit and receive when it is within the yellow circles on the figures. The grid shows 15° lines for both latitude and longitude. Figure A.4-1: Global View of Athena Satellite TT&C Coverage Area 4

REDACTED FOR PUBLIC INSPECTION Figure A.4-2: Zoom View of Athena Satellite TT&C Coverage Area Figure A.4-3 and Figure A.4-4 show the coverage areas of the Athena satellite E-band for minimum elevation angles of 30° and 10°, respectively. The spacecraft will only transmit and receive when it is within the green circles on the figures. The grid shows 15° lines for both latitude and longitude. 5

REDACTED FOR PUBLIC INSPECTION Figure A.4-3: View of Athena Satellite E-Band Coverage Area for 30° Minimum Elevation Angle Figure A.4-4: View of Athena Satellite E-Band Coverage Area for 10° Minimum Elevation Angle 6

REDACTED FOR PUBLIC INSPECTION A.5 Calculated Maximum Power Flux Density Levels (§25.114(c)(8)) The Athena satellite’s TT&C downlink operations in part of the 8025-8500 MHz band comply with the ITU Power Flux Density (“PFD”) limits applicable to that band. Table A.5-1 shows the ITU PFD limits in the band. Table A.5-1: ITU Power Flux Density Limits in the 8025 – 8500 MHz Band PFD Limit in dB(W/m2) for angles of arrival (δ) above the horizontal plane Reference Frequency range bandwidth 0°-5° 5°-25° 25°-90° 8025 – 8500 MHz -150 −150 + 0.5(δ − 5) −140 4 kHz The Athena satellite TT&C downlink has a maximum transmit EIRP of 3.64 dBW and a bandwidth of 2.3 MHz. Table A.5-2 shows the maximum PFD at the surface of the earth produced by this emission assuming an orbital altitude of 500 km, which would result in the highest PFD levels. Table A.5-2: Maximum Athena PFD in the 8025 – 8500 MHz Band Maximum EIRP (dBW) 3.64 Bandwidth (MHz) 2.3 EIRP Density (dBW/4 kHz) -23.94 Minimum Distance (km) 500 Maximum PFD (dBW/m2/4 kHz) -148.96 Table A.5-3 shows the calculated maximum PFD levels at the surface of the Earth for elevation angles from 5° to 90° along with the margin and demonstrates that the ITU PFD Limit in the 8025- 8500 MHz band is met. Figure A.5-1 shows the graphical comparison of the Athena maximum PFD levels to the ITU PFD limits. 7

REDACTED FOR PUBLIC INSPECTION Table A.5-3: X-Band TT&C Downlink Compliance with ITU PFD Limits in the 8025-8500 MHz Band PFD with Peak Antenna Gain Margin to Elevation ITU PFD Limit (dBW/m2 / ITU PFD Angle (°) (dBW/m2 / 4kHz) 4kHz) Limit (dB) 5 -150.00 -160.78 10.78 10 -147.50 -159.31 11.81 15 -145.00 -157.70 12.70 20 -142.50 -156.26 13.76 25 -140.00 -155.00 15.00 30 -140.00 -153.91 13.91 35 -140.00 -152.95 12.95 40 -140.00 -152.13 12.13 45 -140.00 -151.65 11.65 50 -140.00 -151.04 11.04 55 -140.00 -150.52 10.52 60 -140.00 -150.09 10.09 65 -140.00 -149.73 9.73 70 -140.00 -149.44 9.44 75 -140.00 -149.22 9.22 80 -140.00 -149.06 9.06 85 -140.00 -148.97 8.97 90 -140.00 -148.96 8.96 8

REDACTED FOR PUBLIC INSPECTION Figure A.5-1: PFD Levels from the Athena TT&C Downlink compared with ITU Limits -135 -140 -145 PFD (dBW/m2/4 kHz) -150 ITU PFD Limits -155 Calculated Athena PFD -160 -165 0 10 20 30 40 50 60 70 80 90 Elevation Angle (degrees) There are no ITU or FCC PFD limits in the 71-76 GHz band. In this band, the Athena satellite has a maximum transmitted EIRP of 44.3 dBW and a bandwidth of 2.1852 GHz. Table A.5-4 shows the maximum PFD at the surface of the earth produced by this emission. Table A.5-5 shows the calculated maximum PFD levels for elevation angles from 10° to 90°. 9

REDACTED FOR PUBLIC INSPECTION Table A.5-4: Maximum Athena Satellite PFD at the Surface of the Earth in the 71 - 76 GHz Band Maximum EIRP (dBW) 44.3 Bandwidth (GHz) 2.1852 EIRP Density (dBW/4 kHz) -113.07 Minimum Distance (km) 500 Maximum PFD (dBW/m2/4 kHz) -138.05 Table A.5-5: Maximum Athena PFD in the 71 - 76 GHz Band at Various Elevation Angles Elevation PFD with Peak Antenna Gain Angle (°) (dBW/m2/4 kHz) 10 -148.65 15 -147.04 20 -145.60 25 -144.34 30 -143.24 35 -142.29 40 -141.47 45 -140.76 50 -140.15 55 -139.63 60 -139.19 65 -138.83 70 -138.54 75 -138.32 80 -138.17 85 -138.08 90 -138.05 5.a X-Band TT&C Compliance with Deep Space Protection Limits According to the ITU Radio Regulations, the 8400-8450 MHz band is allocated to the Space Research Service in the space-to-Earth direction and the use of the band is limited to satellites that are orbiting in deep space. Recommendation ITU-R SA.1157-1 (“Protection criteria for deep- space research”) gives the maximum allowable interference power into deep-space receiving earth stations and the interference protection criteria for deep-space earth stations in the 8400-8425 GHz frequency band. The following is an excerpt from the ITU-R Recommendation: 10

REDACTED FOR PUBLIC INSPECTION ______________________________________________________________________________ Recommendation ITU-R SA.1157-1 TABLE 4 Maximum allowable interference power to earth-station receivers Maximum noise-like Receiver noise spectral Maximum CW Band interference power density interference power (GHz) spectral density (dB(W/Hz)) (dBW) (dB(W/Hz)) 2.29-2.30 –216.6 –221.6 –222.5 8.40-8.45. –215.0 –220.0 –220.9 12.75-13.25 –214.6 –219.6 –220.5 31.8-32.3 –211.4 –216.4 –217.3 Protection criteria for deep-space earth-station receivers Table 5 gives the maximum allowable interference that will not cause more than the acceptable degradation of earth-station receiver performance. These values are the protection criteria for a deep-space earth-station receiver at the receiver input terminals: greater interference is harmful. Also shown is the corresponding power spectral flux-density at the aperture of a 70 m diameter reflector antenna. The antenna has approximately 70% area efficiency for the lower bands and 40% at 32 GHz. Recommendation ITU-R SA.1157-1 TABLE 5 Interference protection for deep-space earth-stations Maximum allowable interference power Maximum allowable interference power Band spectral density spectral flux-density (GHz) (dB(W/Hz)) (dB(W/m2 · Hz)) 2.29-2.30 –222.5 –257.0 8.40-8.45 –220.9 –255.1 12.75-13.25 –220.5 –254.3 31.8-32.3 –217.3 –249.3 To protect earth-station receivers, the power spectral density of noise-like interference, or the total power of CW interference, should not be greater than the amount shown in Table 5. ______________________________________________________________________________ 11

REDACTED FOR PUBLIC INSPECTION The Athena satellite X-band telemetry carrier is centered at a frequency of 8496.25 MHz. Tests were performed to determine the interference levels that would be received at a deep-space earth station operating in the 8400-8450 MHz band. Table A.5.a-1 shows the maximum power level at the surface of the earth under clear-sky conditions at the Athena satellite TT&C center frequency. Table A.5.a-1: Maximum Power Level at the Surface of the Earth at TT&C Center Frequency Telemetry (Downlink) Budget 5 deg El 10 deg El 45 deg El 90 deg El Parameter (Peak) (Peak) (Peak) (Peak) Unit Frequency 8.49625 8.49625 8.49625 8.49625 GHz Altitude 500 500 500 500 km Elevation Angle 5 10 45 90 deg Slant Range 2077.96 1695.09 683.09 500.00 km Range Factor 137.34 135.58 127.68 124.97 dB Aperture Factor 40.03 40.03 40.03 40.03 dB Path Loss -177.38 -175.61 -167.72 -165.01 dB Atmospheric Loss -0.6 -0.3 -0.07 -0.05 dB Tx Power 2.5 2.5 2.5 2.5 W in dBW 3.98 3.98 3.98 3.98 dBW S/C Antenna Gain 5.5 5.5 5.5 5.5 dBi Tx Loss -5.84 -5.84 -5.84 -5.84 dB Transmit EIRP 3.64 3.64 3.64 3.64 dBW Transmit EIRP (W) 2.31 2.31 2.31 2.31 W Pol Loss 0 0 0 0 dB Power at E/S -174.34 -172.27 -164.15 -161.42 dBW Figure A.5.a-1 shows the test data for the X-band TT&C spurious emissions spectrum down to 8.44 GHz. 12

REDACTED FOR PUBLIC INSPECTION Figure A.5.a-1: X-band Telemetry Spurious Emissions Spectrum 13

REDACTED FOR PUBLIC INSPECTION As shown in Table A.5.a-1, the power level at the Earth’s surface at 8496.25 MHz is -164.1 dBW. The CW interference level roll-off from the modulated spectrum peak at the edge of the deep-space band (8450 MHz) is 67 dBc. Thus, the maximum CW interference power in the deep-space band is -228.4 dBW, which is 8.4 dB below the maximum CW interference power given in Table 4 of ITU Recommendation SA.1157-1. The peak PFD at the Earth’s surface of the Athena satellite X- band downlinks is -185.0 dBW/m2/Hz. The measurements show the test equipment noise floor at -82 dBc, which results in a PFD in the deep-space band of -267 dBW/m2/Hz, which is 11.9 dBW less than the protection level given in the ITU Recommendation. Similarly, the noise-like interference based on a peak power spectral density of -225.0 dBW/Hz and a noise floor of -82 dBc results in a maximum noise-like interference of -307.0 dBW/Hz, which is 86.1 dB less than the protection values given in the ITU Recommendation. Table A.5.a-2 shows that that Athena satellite X-band downlinks are compliant with the deep-space protection criteria. Table A.5.a-2: Athena Satellite Compliance with Deep Space Protection Criteria A.6 Overall Description of System Facilities, Operations and Services (§25.114(d)(1)) The Athena experiment includes one non-GSO satellite operating in the E-band (71-76 GHz for downlink and 81-86 GHz for uplink) communicating with earth stations located in the southwest United States. The TT&C for the satellite will be conducted in the X-band for downlink and S- band for uplink and will use three specific earth stations. Due to the nature of the non-geostationary orbit, there will be limited time during the orbit that the satellite is visible to one of its earth stations. Additionally, the duration of this visibility will be relatively short. For the E-band communications, the transmissions will be for less than 8 minutes per contact and there will be up to two contacts per day at an elevation angle greater than or equal to 30°, which may increase to four contacts a day for experiments at an angle lower than 30° and greater than or equal to 10°. For the TT&C communications, the transmissions will be less than 10 minutes per contact. There will be up to ten contacts per day for the TT&C downlinks, and up to three contacts per day for the TT&C uplinks. The TT&C coverage areas are shown in Section A.4 of this Exhibit. 14

REDACTED FOR PUBLIC INSPECTION Table A.6-1 gives the maximum amount of time (in seconds) the Athena satellite will transmit and receive above a given minimum elevation angle during the longest pass over the TT&C and E-band ground stations. E-band link “baseline” testing will nominally occur above 30° minimum elevation angles, with the primary goal of demonstrating high rate links up to 4.5 minutes in duration, per contact, to an earth station through a variety of atmospheric conditions, enabling the validation of ITU models. E-band “goal” testing will occur above 20° minimum elevation angles for up to 5.3 minutes to study the effects of additional atmospheric attenuation. E-band “stretch” testing will occur above 10° minimum elevation angles for up to 8.0 minutes to study maximum attenuation effects. Less than six contacts per month are planned to be goal or stretch tests that apply minimum elevation angles less than 30°. Table A.6-1: Maximum Pass Time (in Seconds) for Different Minimum Elevation Angles Minimum Maximum Pass Maximum Pass Notes Elevation Time 500 km Time 550km Angle altitude altitude 5° 552.4 589.6 TT&C: Brewster, Mojave, Albuquerque 10 ° 443.0 476.9 E-band (stretch test): LA/Ventura Counties (see A.6.a) 20 ° 295.8 322.2 E-band (goal test): LA/Ventura Counties (see A.6.a) 30 ° 207.4 227.3 E-band (baseline test): LA/Ventura Counties (see A.6.a) A.6.a Description of Satellite, including Antenna Patterns for both E-band and TT&C For the TT&C, there is a single S/X-band transceiver on the satellite with internal transmit signal amplification. The receiver is always ON; the transmitter is only ON when in the field-of-view of the TT&C ground stations above the respective minimum elevation angles. There are two receive S-band patch antennas for command and two transmit X-band patch antennas for telemetry. Both command and telemetry use right-hand circular polarization. The gain patterns for these antennas are given in Figure A.6.a-1 and A.6.a-2. Table A.6.a-1 provides a description of each of the TT&C earth stations. 15

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-1 TT&C Satellite Antenna Transmit Pattern 16

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-2 TT&C Satellite Antenna Receive Pattern Table A.6.a-1 Description of TT&C Earth Stations Location Mojave, CA Albuquerque, NM Brewster, WA Latitude (°N) 35.064 35.054 48.145 Longitude (°E) -118.162 -106.619 -119.7 Antenna Size 3.0 m (Rx/Tx S-band, 3.0 m S-band Rx/Tx 7.6m (Rx/Tx) Rx X-band) 4.5m X-band Tx Maximum Uplink EIRP 45 dBW 45 dBW 48 dBW Earth Station Antenna 34 dBi 34 dBi 42.2 dBi Maximum Transmit Gain Reference Antenna See Figure A.6.a-3 See Figure A.6.a-3 Meets reference Pattern radiation pattern set forth in Recommendation ITU- 17

REDACTED FOR PUBLIC INSPECTION R S.465-6. Polarization RHCP RHCP RHCP Minimum Elevation 5° 5° 5° Angle Maximum Pass Length 590 seconds 590 seconds 590 seconds Maximum Passes Per 3 to 4 3 to 4 4 to 5 Day Figure A.6.a-3 TT&C 3.0 meter Earth Station Antenna Transmit Pattern The maximum uplink EIRP for the TT&C command link will be 48 dBW for the Brewster earth station and 45 dBW for the Mojave and Albuquerque earth stations. The data rate will be 256 kbps. Right-hand circular polarization will be used for the command signal. Table A.6.a-2 shows the link budget for the command. These link budgets are for an EIRP level of 45 dBW. For the 48 dBW EIRP uplink from the Brewster earth station, the link will close with additional margin. 18

REDACTED FOR PUBLIC INSPECTION Table A.6.a-2: TT&C Command Link Budget 5 deg El 10 deg El 45 deg El 90 deg El Parameter (Peak) (Peak) (Peak) (Peak) Unit Frequency 2.082 2.082 2.082 2.082 GHz Altitude 500 500 500 500 km Elevation Angle 5 10 45 90 deg Slant Range 2077.96 1695.09 683.09 500.00 km Range Factor 137.34 135.58 127.68 124.97 dB Aperture Factor 27.82 27.82 27.82 27.82 dB Path Loss -165.16 -163.40 -155.50 -152.79 dB Atmospheric Loss -0.45 -0.23 -0.06 -0.04 dB E/S Uplink EIRP 45.00 45.00 45.00 45.00 dBW Pol Loss 0 0 0 0 dB 2 Uplink Flux Density -92.34 -90.81 -82.74 -80.01 dBW/m S/C ANT Gain 6.8 6.8 6.8 6.8 dBi Signal Power at Antenna Hardline Interface -113.81 -111.83 -103.76 -101.03 dBW RX Input Loss -4.62 -4.62 -4.62 -4.62 dB Signal Power at RX Input -88.44 -86.45 -78.38 -75.65 dBm Min Acquire Threshold -103.00 -103.00 -103.00 -103.00 dBm Margin without Interference 14.56 16.55 24.62 27.35 dB C/X Isolation at Antenna 8.00 8.00 8.00 25.00 dB Interf Gain @ Opposite Antenna -6.00 -6.00 -6.00 -30.00 dBi Interf Pwr at Rx Input, Total RSS -101.11 -99.12 -91.05 -111.84 dBm Signal Power at Rcvr Input, Interference Degraded -88.68 -86.69 -78.63 -75.65 dBm Margin to Threshold, WC Intf Degraded 14.32 16.31 24.37 27.35 dB Command Rcvr Noise Figure 3.5 3.5 3.5 3.5 dB Noise Density -170.48 -170.48 -170.48 -170.48 dBm/Hz C/No, WC Intf Degraded 81.80 83.79 91.85 94.82 dB-Hz -10 Eb/No @ 10 BER 13 13 13 13 dB Implementation Loss 2 2 2 2 dB Bit rate 256 256 256 256 kbps Bit rate BW 54.08 54.08 54.08 54.08 dB-Hz Required S/No 69.08 69.08 69.08 69.08 dB-Hz BER Margin 12.72 14.70 22.77 25.74 dB The data rate for the telemetry link is 512 kbps with a maximum transmitter output power of 2.5 Watts. The peak antenna gain is 5.5 dBi. Right-hand circular polarization will be used for the telemetry signal. The maximum EIRP after losses is 3.64 dBW. Table A.6.a-3 shows the link budget for the telemetry link. These link budgets are for the Mojave and Albuquerque 3.0 meter earth station antennas. Again, for the Brewster 7.6 meter antenna, the link will close with additional margin due to the higher on-axis gain. 19

REDACTED FOR PUBLIC INSPECTION Table A.6.a-3: TT&C Telemetry Link Budget 5 deg El 10 deg El 45 deg El 90 deg El Parameter (Peak) (Peak) (Peak) (Peak) Unit Frequency 8.49625 8.49625 8.49625 8.49625 GHz Altitude 500 500 500 500 km Elevation Angle 5 10 45 90 deg Slant Range 2077.96 1695.09 683.09 500.00 km Range Factor 137.34 135.58 127.68 124.97 dB Aperture Factor 40.03 40.03 40.03 40.03 dB Path Loss -177.38 -175.61 -167.72 -165.01 dB Atmospheric Loss -0.6 -0.3 -0.07 -0.05 dB Tx Power 2.5 2.5 2.5 2.5 W in dBW 3.98 3.98 3.98 3.98 dBW S/C Antenna Gain 5.5 5.5 5.5 5.5 dBi Tx Loss -5.84 -5.84 -5.84 -5.84 dB Transmit EIRP 3.64 3.64 3.64 3.64 dBW Transmit EIRP (W) 2.31 2.31 2.31 2.31 W Pol Loss 0 0 0 0 dB Power at E/S -174.34 -172.27 -164.15 -161.42 dBW C/X Isolation at S/C Antenna 5.00 5.00 5.00 8.00 Interf Gain @ Opposite Antenna -6.00 -6.00 -6.00 -30.00 dBi E/S G/T 25 25 25 25 dB/K Downlink C/No 79.26 81.33 89.45 92.18 dB-Hz Downlink C/No, Intf Degraded 78.92 80.99 89.12 92.17 dB-Hz -6 Reqd Eb/No @ 10 BER 10.5 10.5 10.5 10.5 dB Coding Gain 5.5 5.5 5.5 5.5 dB Implementation Loss 2 2 2 2 dB Bit rate 512 512 512 512 Kbps Bit rate BW 57.09 57.09 57.09 57.09 dB-Hz Required S/No 64.09 64.09 64.09 64.09 dB-Hz Link Margin 14.83 16.90 25.02 28.08 dB For the E-band, there is one antenna onboard the spacecraft. This antenna is a parabolic, Axially Displaced Ellipse (ADE) with a diameter of 50 cm. The maximum transmit gain for this antenna is 49.7 dBiC and the maximum receive gain is 50.7 dBiC. Both right-hand circular and left-hand circular polarizations will be used for the uplink and downlink transmissions. The satellite transmit antenna gain patterns are shown in Figures A.6.a-4 and A.6.a-5. The satellite receive antenna gain patterns are shown in Figures A.6.a-6 and A.6.a-7. The uplink transmissions are received at center frequencies of 82 GHz and 85 GHz and the downlink transmissions are sent at center frequencies of 72 GHz and 75 GHz. The occupied bandwidth for these carriers is 2.185 GHz. The satellite will normally only transmit and receive when the elevation angle from the earth station to the satellite is greater than or equal to 30°; however, there are some specific experiments in which the minimum elevation angle will be 10°. 20

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-4 Athena E-Band Satellite Antenna Transmit Pattern (RHCP) Figure A.6.a-5 Athena E-Band Satellite Antenna Transmit Pattern (LHCP) 21

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-6 Athena E-Band Satellite Antenna Receive Pattern (RHCP) Figure A.6.a-7 Athena E-Band Satellite Antenna Receive Pattern (LHCP) 22

REDACTED FOR PUBLIC INSPECTION At the present time, there are three potential E-band earth station locations and two of these will be selected to be used for the Athena satellite in the first half of 2018. Table A.6.a-4 gives the technical parameters and pass information for the E-band earth stations. Table A.6.a-4: Description of E-Band Earth Stations Location Northridge, Los Angeles Santa Paula, California County (Mt. California Wilson) Latitude (°N) 34.224241 34.224889 34.402443 Longitude (°E) -118.500349 -118.056639 -119.072900 Antenna Size 1.2 m 2.4 m 2.4 m Maximum 58.0 dBi 65.8 dBi 65.8 dBi Antenna Gain Reference See Figure See Figures See Figures Antenna Pattern A.6.a-8 A.6.1.a-9 and A.6.1.a-9 and A.6.a-10 A.6.a-10 Nominal 30 30 30 Minimum Elevation Angle Maximum Pass 228 228 228 Length at Nominal (477) (477) (477) Minimum Elevation Angle (and at 10°elevation) Passes Per Day Up to 2 Up to 2 Up to 2 23

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-8 Earth Station Pattern for 1.2m Ground Antenna at 76 GHz and 86 GHz 24

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-9: LHCP Earth Station Antenna Pattern for 2.4 Meter Antenna at 83 GHz 25

REDACTED FOR PUBLIC INSPECTION Figure A.6.a-10: LHCP Earth Station Principal Plane Pattern Cuts for 2.4 Meter Antenna at 83 GHz (Peak Gain: 65.8 dBiC) The baseline link budgets for the E-band uplink and downlink using a 2.4 meter earth station antenna are given in Table A.6.a-5. The baseline link budgets for the E-band uplink and downlink using a 1.2 meter backup earth station antenna are given in Table A.6.a-6. For the uplink, a higher power option for the primary earth station’s 2.4 m antenna may be applied at the midpoint of the mission. This higher power uplink would substitute (50W) traveling wavetube amplifiers (TWT) for the existing solid-state earth station power amplifiers as a demonstration of the viability of commercial E-band TWTs for space-based communication systems to drive higher link data rates, which has not previously been publicly demonstrated. The higher power 2.4 m antenna will observe the same general operational principles as the initially deployed antenna (e.g., number of passes, pass duration, elevation angles). 26

REDACTED FOR PUBLIC INSPECTION Table A.6.a-5: E-Band Link Budgets using 2.4 meter Earth Station Antenna Link Parameter Downlink Uplink HP Opt. Carrier Frequency 72.0GHz 75.0GHz 82.0GHz 85.0GHz 82.0GHz 85.0GHz Wavelength 0.0042m 0.0040m 0.0037m 0.0035m 0.0037m 0.0035m RRC Roll-Off Factor α=0.37 α=0.37 α=0.37 α=0.37 α=0.37 α=0.37 Symbol Rate 1.595GSps 1.595GSps 1.595GSps 1.595GSps 1.595GSps 1.595GSps Occupied Bandwidth 2.185GHz 2.185GHz 2.185GHz 2.185GHz 2.185GHz 2.185GHz Information Rate (/Ch/Pol) 2.65Gbps 2.65Gbps 2.65Gbps 2.65Gbps 7.94Gbps 7.94Gbps TX Power Amplifier P1dB 30.0dBm 30.0dBm 33.0dBm 33.0dBm 47.0dBm 47.0dBm Output Back-Off (OBO) 3.8dB 3.8dB 3.8dB 3.8dB 7.5dB 7.5dB Post PA Losses 1.55dB 1.55dB 1.55dB 1.55dB 1.55dB 1.55dB Transmitted Power POut 24.6dBm 24.6dBm 27.6dBm 27.6dBm 37.9dBm 37.9dBm Transmit Antenna Aperture 0.50m 0.50m 2.40m 2.40m 2.40m 2.40m Half-power beamwidth 0.583° 0.560° 0.107° 0.103° 0.107° 0.103° Transmit Aperture Efficiency 60% 60% 84% 84% 84% 84% Transmit Antenna Gain 49.3dBi 49.7dBi 65.5dBi 65.8dBi 65.5dBi 65.8dBi EIRP 73.9dBm 74.3dBm 93.1dBm 93.4dBm 103.4dBm 103.8dBm Transmit Antenna Pointing Loss 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB Radome Loss 0.00dB 0.00dB 1.07dB 1.09dB 1.07dB 1.09dB Link Distance Slant Range 909km 909km 909km 909km 909km 909km Free Space Loss 188.8dB 189.1dB 189.9dB 190.2dB 189.9dB 190.2dB Propagation Loss 8.60dB 8.60dB 5.5dB 5.5dB 5.5dB 5.5dB Total Path Loss (Less Radomes) 197.4dB 197.7dB 195.4dB 195.7dB 195.4dB 195.7dB Radome Loss 1.25dB 1.17dB 0.00dB 0.00dB 0.0dB 0.0dB Received Power at Antenna -125.2dBm -125.1dBm -103.8dBm -103.8dBm -93.5dBm -93.5dBm Receive Antenna Aperture 2.40m 2.40m 0.50m 0.50m 0.50m 0.50m Receive Antenna Efficiency 84% 84% 60% 60% 60% 60% Receive Antenna Gain 64.4dBi 64.7dBi 50.4dBi 50.7dBi 50.4dBi 50.7dBi Receive Antenna Pointing Loss 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB Feed Loss 0.10dB 0.10dB 0.10dB 0.10dB 0.10dB 0.10dB Post-Feed Losses 1.55dB 1.55dB 1.45dB 1.45dB 1.45dB 1.45dB Received Power at LNA Input -63.0dBm -62.5dBm -55.5dBm -55.2dBm -45.1dBm -44.8dBm Receiver Noise Temperature 438.4K 438.4K 438.4K 438.4K 438.4K 438.4K System Noise Temperature 697.0K 697.0K 668.0K 668.0K 668.0K 668.0K Carrier to Noise (C/N) 15.2dB 15.6dB 22.9dB 23.2dB 33.2dB 33.5dB Carrier to Interference (C/I) 40.0dB 40.0dB 40.0dB 40.0dB 40.0dB 40.0dB Antenna Cross-Pol Isolation 35.0dB 35.0dB 35.0dB 35.0dB 35.0dB 35.0dB C/(N+I) 15.1dB 15.6dB 22.5dB 22.8dB 30.5dB 30.6dB Link margin (dB) 5.9dB 6.4dB 13.3dB 13.6dB 8.2dB 8.3dB Total information rate (Gb/s) 10.59Gbps 10.59Gbps 10.59Gbps 10.59Gbps 31.77Gbps 31.77Gbps 27

REDACTED FOR PUBLIC INSPECTION Table A.6.a-6: E-Band Link Budgets for using 1.2 meter Backup Earth Station Antenna Link Parameter Downlink Uplink HP Opt. Carrier Frequency 72.0GHz 75.0GHz 82.0GHz 85.0GHz 82.0GHz 85.0GHz Wavelength 0.0042m 0.0040m 0.0037m 0.0035m 0.0037m 0.0035m RRC Roll-Off Factor α=0.37 α=0.37 α=0.37 α=0.37 α=0.37 α=0.37 Symbol Rate 1.595GSps 1.595GSps 1.595GSps 1.595GSps 1.595GSps 1.595GSps Occupied Bandwidth 2.185GHz 2.185GHz 2.185GHz 2.185GHz 2.185GHz 2.185GHz Information Rate (/Ch/Pol) 2.65Gbps 2.65Gbps 2.65Gbps 2.65Gbps 7.94Gbps 7.94Gbps TX Power Amplifier P1dB 30.0dBm 30.0dBm 33.0dBm 33.0dBm 47.0dBm 47.0dBm Output Back-Off (OBO) 3.8dB 3.8dB 3.8dB 3.8dB 7.5dB 7.5dB Post PA Losses 1.55dB 1.55dB 1.55dB 1.55dB 1.55dB 1.55dB Transmitted Power POut 24.6dBm 24.6dBm 27.6dBm 27.6dBm 37.9dBm 37.9dBm Transmit Antenna Aperture 0.50m 0.50m 1.20m 1.20m 1.20m 1.20m Half-power beamwidth 0.583° 0.560° 0.213° 0.206° 0.213° 0.206° Transmit Aperture Efficiency 60% 60% 55% 55% 55% 55% Transmit Antenna Gain 49.3dBi 49.7dBi 57.7dBi 58.0dBi 57.7dBi 58.0dBi EIRP 73.9dBm 74.3dBm 85.3dBm 85.6dBm 95.6dBm 95.9dBm Transmit Antenna Pointing Loss 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB Radome Loss 0.00dB 0.00dB 1.07dB 1.09dB 1.07dB 1.09dB Link Distance Slant Range 909km 909km 909km 909km 909km 909km Free Space Loss 188.8dB 189.1dB 189.9dB 190.2dB 189.9dB 190.2dB Propagation Loss 8.60dB 8.60dB 5.5dB 5.5dB 5.5dB 5.5dB Total Path Loss (Less Radomes) 197.4dB 197.7dB 195.4dB 195.7dB 195.4dB 195.7dB Radome Loss 1.25dB 1.17dB 0.00dB 0.00dB 0.0dB 0.0dB Received Power at Antenna -125.2dBm -125.1dBm -111.7dBm -111.7dBm -101.4dBm -101.4dBm Receive Antenna Aperture 1.20m 1.20m 0.50m 0.50m 0.50m 0.50m Receive Antenna Efficiency 55% 55% 60% 60% 60% 60% Receive Antenna Gain 56.5dBi 56.9dBi 50.4dBi 50.7dBi 50.4dBi 50.7dBi Receive Antenna Pointing Loss 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB 0.50dB Feed Loss 0.10dB 0.10dB 0.10dB 0.10dB 0.10dB 0.10dB Post-Feed Losses 1.55dB 1.55dB 1.45dB 1.45dB 1.45dB 1.45dB Received Power at LNA Input -70.8dBm -70.4dBm -63.3dBm -63.0dBm -53.0dBm -52.7dBm Receiver Noise Temperature 438.4K 438.4K 438.4K 438.4K 438.4K 438.4K System Noise Temperature 697.0K 697.0K 668.0K 668.0K 668.0K 668.0K Carrier to Noise (C/N) 7.3dB 7.8dB 15.0dB 15.3dB 25.4dB 25.7dB Carrier to Interference (C/I) 40.0dB 40.0dB 40.0dB 40.0dB 40.0dB 40.0dB Antenna Cross-Pol Isolation 35.0dB 35.0dB 35.0dB 35.0dB 35.0dB 35.0dB C/(N+I) 7.3dB 7.8dB 15.0dB 15.3dB 24.8dB 25.0dB Link margin (dB) -1.9dB -1.4dB 5.8dB 6.1dB 2.5dB 2.7dB Total information rate (Gb/s) 10.59Gbps 10.59Gbps 10.59Gbps 10.59Gbps 31.77Gbps 31.77Gbps 28

REDACTED FOR PUBLIC INSPECTION A.7 The Complete Program of Research and Experimentation Proposed, Including a Description of Equipment and Theory of Operation (Form 442 – Question 7a, §5.63(c)(1)) Space Systems/Loral (“SSL”) is the manufacturer of the Athena satellite. The satellite consists of an SSL 100 bus customized to accommodate the Athena payload. Spacecraft mass is 150 kg and volume approximately 0.33 cubic meters. The spacecraft bus is a three-axis stabilized bus providing attitude control, power and communication channels to the payload. To support payload activities, the bus will steer the spacecraft body towards a ground station, maintain pointing throughout the payload operations, and provide the necessary power for the payload to operate. During that entire time, the spacecraft will be in contact with the ground providing telemetry and responding to commands. After payload activities are completed, the spacecraft will return to a Sun pointing attitude that will allow its batteries to recharge in preparation for the subsequent payload activity. Power is nominally only provided to the payload during predetermined and commanded payload pass opportunities that align with contacts to the ground stations noted in Table A.6.a-4. In addition, as the spacecraft passes in view of TT&C ground stations noted in Table A.6.a-1 (outside of payload activities), it will download stored telemetry to the ground as well as provide uplink opportunities for commands and uploads in preparation of subsequent payload activities. Table A.7-1 and Table A.7-2 give the equipment characteristics for the TT&C receiver and TT&C transmitter, respectively. 29

REDACTED FOR PUBLIC INSPECTION Table A.7-1 TT+C Receiver Characteristics Parameter Value Signal Level Range ≤ –100 dBm to ≥ –47 dBm Signal Sweep Range fR ±90 kHz ≤ –100 dBm at 1 kHz/s, 5 kHz/s Acquisition Threshold ≤ –90 dBm at 1 kHz/s, 5 kHz/s, 10 kHz/s RF Carrier Frequency 2082 MHz Data Rate 256 kbps Modulation BPSK modulation on carrier Command Threshold with BER ≤ –100 dBm at RF input of 10-6) Command Signal Level ≤ –100 dBm to ≥ –47 dBm at RF input Table A.7-2 TT+C Transmitter Characteristics 30

REDACTED FOR PUBLIC INSPECTION The E-band transceivers on the satellite and at the ground station are both of the direct- conversion I/Q modulation type (i.e., baseband signals are modulated/demodulated directly onto/from the E-band carriers via I/Q mixers). After modulation on the carriers, each transmit channel is routed through individual gain stages and power amplifiers before being combined and diplexed through the transceiver multiplexer. The receive paths are identical, but in reverse, and instead of power amplifiers, low noise amplification is utilized between the antenna port and the demodulator. The primary differences between the transceiver on the spacecraft and that in the ground station are (1) the transmit and receive bands are swapped and (2) there are higher- power amplifiers on the ground for the uplink signals. Key specification parameters at the air interfaces for these transceivers are provided in Table A.7-3. Table A.7-3 E-band Transmitter Details Key Performance Parameter Specification Comment Downlink: 72 & 75GHz Carrier Frequencies Uplink: 82 & 85GHz Downlink: +24.6 dBm Maximum Transmitter RF Uplink: +27.6 dBm Output Power Uplink HP Option: 37.9 As mentioned above and indicated in dBm Tables A.6.a-5 and A.6.a-6, an optional Downlink: 74.3 dBm 50W (+47 dBm) TWTA may be used late in the mission for the uplink. Uplink: 93.4 dBm Maximum Transmit EIRP Uplink HP Option: 103.8 dBm ≤±4ppm/Temperature Carrier Frequency Accuracy ≤±1ppm/1st year, ≤±5ppm/10 years Carrier Phase Noise 1MHz Offset: Applies to both transmit carrier and receive ≤-95dBc/Hz local oscillator signal (at E-band) Integrated over 1-50MHz ≤-38dBc offset: QPSK, 8APSK, 16QAM, 32QAM & RF Modulation I/Q Modulation 64QAM Pre-Mod RRC Roll-Off 0.37 nominal Data Symbol Rate 1.595 GSps 31

REDACTED FOR PUBLIC INSPECTION A.8 Cessation of Emissions (§25.207) The satellite transmissions can be turned on and off by ground telecommand, thereby causing cessation of emissions from the satellite, as required by §25.207 of the Commission's rules. For the payload, the spacecraft simply cuts the power supply to the payload modules, inhibiting any transmission of emissions; this is true for any time that the system is not executing a payload contact to a ground station noted in A.6.a-4. For the TT&C chain, although the receiver part of the transceiver is always expected to be on (when battery charge exceeds a certain state-of- charge) in order to receive commands, the transmitter chain is commandable and can be turned off to prevent any transmission of emissions. The spacecraft power distribution unit has “end of mission” switches that inhibit charging of the battery, causing a slow decay of the state of charge until ultimate passivation. The end of mission switches are commandable (both ways), and the effect of closing the switches is slow enough to allow reversal in case of inadvertent commanding. 32


Document Created: 2019-03-13 09:30:12
Document Modified: 2019-03-13 09:30:12
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