Exhibit 2 BRIO Technical RevA

0220-EX-CN-2018 Text Documents

SpaceQuest, Ltd.

2018-05-09ELS_209374

BRIO Satellite

Exhibit 2

File #: 0220-EX-CN-2018

Technical Information

March 7, 2018
May 8, 2018 (Rev A)

Submitted By

SpaceQuest, Ltd.
3554 Chain Bridge Road
Suite 400
Fairfax, VA 22030

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

Table of Contents
1 Ownership, Operations and Construction. ..................................................................... 3
2 Orbital Requirements. ................................................................................................... 3
3 Service Area. ................................................................................................................. 3
4 Satellite Payload. .......................................................................................................... 3
5 Principle Specifications. ................................................................................................. 4
6 System Block Diagram. .................................................................................................. 4
7 Telemetry, Tracking & Command and Payload Operations ............................................. 6
8 Radio Equipment. .......................................................................................................... 6
8.1 UHF TT&C Transceiver ........................................................................................................6
8.2 VHF Receiver: ....................................................................................................................7
8.3 S-Band Transceiver:............................................................................................................7
8.4 UHF Experimental Payload Transceiver ...............................................................................7
9 Antenna Systems........................................................................................................... 8
10 Satellite Link Budgets .................................................................................................... 9
11 Interference Analysis................................................................................................... 14
11.1 400.50-400.65 MHz (TT&C and Experimental Downlink) .................................................... 14
11.2 399.90 -400.05 MHz (TT&C and Experimental Uplink) ........................................................ 14
11.3 2200-2290 MHz (Payload Downlink) ................................................................................. 14
11.4 2025-2110 MHz (Payload Uplink) ...................................................................................... 15
12 Power Flux Density Analysis ........................................................................................ 15
12.1 400.50-400.65 MHz (TT&C Downlink) ............................................................................... 15
12.2 2200-2290 MHz (S-Band Downlink)................................................................................... 16
12.3 400.50-400.65 MHz (Experimental Payload Downlink) ...................................................... 16
13 Space Station Antenna Radiation Patterns ................................................................... 17
13.1 S-Band: BRIO Space Station Transmit/Receive Antenna .................................................... 17
13.2 UHF: BRIO Space Station TT&C Transmit/Receive Antenna ................................................ 17
13.3 VHF: BRIO Space Station Receive Antenna ........................................................................ 18
13.4 UHF: BRIO Space Station Experimental UHF Receive/Transmit Antenna ............................ 18
13.5 Summary of BRIO Antenna Characteristics ........................................................................ 19
14 Earth Station Antenna Radiation Patterns .................................................................... 19
14.1 UHF TT&C Antennas in Fairfax, VA, North Pole, AK, Naalehu, HI and Limestone, ME .......... 19
14.2 VHF Backup Antennas in Fairfax, VA, North Pole, AK, Naalehu, HI and Limestone, ME ....... 20
14.3 S-Band Antennas in Inuvik, Canada and Esrange, Sweden ................................................. 20
14.4 UHF Experimental Antenna .............................................................................................. 21
15 Stop Buzzer POC .......................................................................................................... 21

Exhibit 2 SpaceQuest PAGE 1

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

List of Figures
Figure 1 Orbital Parameters............................................................................................................ 3
Figure 2 System Block Diagram....................................................................................................... 5
Figure 3 Isometric view of deployed configuration. ....................................................................... 5
Figure 4 Summary of BRIO Transmitter and Receiver parameters. ............................................... 8
Figure 5 Antenna Frequency Registration ..................................................................................... 8
Figure 6 Frequency Emissions Registration .................................................................................... 8
Figure 7 Satellite UHF TT&C Uplink Budget .................................................................................... 9
Figure 8 Satellite UHF TT&C Downlink Budget ............................................................................... 9
Figure 9 Satellite S-Band Uplink Budget ....................................................................................... 10
Figure 10 Satellite S-Band Downlink Budget ................................................................................ 10
Figure 11 Satellite Experimental UHF Uplink Budget ................................................................... 11
Figure 12 Satellite Experimental UHF Downlink Budget .............................................................. 11
Figure 13 Satellite VHF Uplink Budget .......................................................................................... 12
Figure 14 Satellite VHF Link Margins Vs. Elevation Angle ............................................................ 12
Figure 15 Satellite UHF TT&C Link Margins Vs. Elevation Angle .................................................. 13
Figure 16 Satellite S-Band Link Margins Vs. Elevation Angle ........................................................ 13
Figure 17 Satellite UHF Experimental Radio Link Margins Vs. Elevation Angle ............................ 14
Figure 18 PFD at the Surface of the Earth for the UHF Transmitter ............................................. 15
Figure 19 PFD at the Surface of the Earth for the S-Band Transmitter ........................................ 16
Figure 20 PFD at the Surface of the Earth for the UHF Payload Transmitter ............................... 16
Figure 21 S-Band Satellite Transmit/Receive Antenna Radiation Pattern ................................... 17
Figure 22 TT&C UHF Satellite Transmit/Receive Antenna Radiation Pattern. ............................. 17
Figure 23 VHF Satellite Receive Antenna Radiation Pattern ........................................................ 18
Figure 24 Experimental UHF Satellite Transmit/Receive Antenna Radiation Pattern ................. 18
Figure 25 BRIO Antenna Characteristics ....................................................................................... 19
Figure 26 UHF Earth Station Antenna Radiation Pattern. ............................................................ 19
Figure 27 VHF Earth Station Antenna Radiation Pattern.............................................................. 20
Figure 28 S-Band Earth Station Antenna Radiation Pattern ......................................................... 20
Figure 29 UHF Experimental Earth Station Antenna Radiation Pattern ....................................... 21

Exhibit 2 SpaceQuest PAGE 2

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

1 Ownership, Operations and Construction.
SpaceQuest, Ltd. is a small business concern, and the owner, manufacturer and operator of
the BRIO satellite. SpaceQuest has selected Spaceflight Industries of Seattle, Washington as
the launch provider. BRIO will be launched on a SpaceX Falcon 9 launch vehicle from
Vandenberg, AFB in California (geographic coordinates 34.5762°N; 4.2803°W) in October 2018.
Pursuant to Part 5 §5.64 of the Commission’s Rules, construction of the proposed
experimental satellite and associated facilities has begun prior to the Commission’s grant of
an authorization. This is necessary given the nature of satellite construction and technical
requirements over long lead times. Such construction is entirely at SpaceQuest’s risk without
any assurances that its proposed experiment will be subsequently approved.
• Space Station Name: BRIO
• BRIO Estimated Construction Completion Date: August 2018
• Spaceflight Final Certification of Licenses (Go/NoGo): September 1, 2018
• Purpose: Experimental, non-Common Carrier basis
• Orbital Type: NGSO

2 Orbital Requirements.
The satellite is designed to operate in a circular sun-synchronous orbit as described in Figure
1. The satellites are based on COTS technology that allows for small, lightweight and low-
cost spacecraft.
BRIO Value
Total Number of Orbital Planes: 1
Celestial Reference Body: Earth
Inclination Angle (degrees): 97.52
Orbital Period (seconds) 5760
Apogee 575 km
Perigee 575 km
Figure 1 Orbital Parameters

3 Service Area.
Worldwide

4 Satellite Payload.
The primary satellite mission of BRIO is to investigate, identify and resolve potential technical
and implementation issues with its advanced satellite SDR radio design developed by
Myriota.
Another important objective is to demonstrate the ability to upload and run new firmware
that can introduce new features to the SDR Radio after it is on orbit. The results of this three-
phase experiment will (1) demonstrate and validate the ability to uplink large numbers of

Exhibit 2 SpaceQuest PAGE 3

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

messages to a satellite using a single channel, (2) demonstrate the ability to downlink
messages to different ground devices on a single channel, and (3) implement an advanced
signal processing algorithm on board a satellite to provide highly spectrally efficient
bidirectional communications.
The secondary satellite mission of BRIO is to test a backup receiver developed by SpaceQuest
to send executive commands, to reboot the satellite flight computer, or to cycle the
spacecraft power bus in the event of a system failure. As a components manufacturer, it is
expected that the outcome of this testing will result in a significant advancement in satellite
radio equipment technology.
The BRIO UHF frequency assignment will be used for satellite telemetry, command and
control. The S-Band assignment will be used to download selected mission data from the
Myriota payload and upload new computer firmware to improve performance and correct
any software deficiencies.

5 Principle Specifications.
BRIO is a 3U CubeSat whose outside envelope measures 100 x 100 x 340.5mm. The satellite’s
total mass is 5 kg. It has four deployable solar arrays, which deploy from the short edges of
the spacecraft. The LiIon battery consists of eight cells wired as 4-series and 2 parallel. The
expected mission lifetime is 5 years in a 575-km orbit due to battery life and deorbit analysis.
SpaceQuest will own and operate the experimental CubeSat throughout its mission lifetime.
The BRIO satellite will not be sold or transferred to another party.

6 System Block Diagram.
Figure 2 below shows the major components of the spacecraft and their interfaces. The flight
computer is responsible for TT&C and payload scheduling. The attitude determination and
control system orients the solar panels to the sun, except when the satellite is re-oriented
to communicate with a ground station. The Software Defined Radio implements the S-Band
transceiver. The deployed array and antenna configuration is shown in Figure 3.

Exhibit 2 SpaceQuest PAGE 4

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

This configuration allows for two VHF and two UHF monopole antennas deployed from the
body of the spacecraft. One UHF antenna is used for TT&C communication. The second UHF
antenna is grounded. A third UHF antenna that is deployed from the side of the satellite
when the solar panels are deployed is for a UHF SDR transceiver, which is a part of the
experimental communications payload being evaluated for the hosted Myriota payload.
The receive-only VHF monopole antennas are used to test a new backup receiver design to
send executive commands to reboot the satellite flight computer in the event of a system
failure.

7 Telemetry, Tracking & Command and Payload Operations
The space-to-Earth downlink frequency band of 400.50-400.65 MHz and the Earth-to-space
uplink frequency band of 399.90-400.05 MHz for TT&C communications will communicate
with SpaceQuest’s Earth stations in Fairfax, Virginia, Naalehu, Hawaii, North Pole, Alaska,
and Limestone, Maine. The SpaceQuest TT&C Earth stations will also have the capability to
uplink executive commands to a backdoor command receiver at 145.92 MHz.
The second UHF Transceiver used to evaluate Myriota’s advanced communications
processor will also operate in the space-to-Earth downlink frequency band of 400.50-400.65
MHz and the Earth-to-space uplink frequency band of 399.90-400.05 MHz.
The space-to-Earth frequency band of 2200-2290 MHz will be used to downlink experimental
test data to Earth Stations in Inuvik, Canada and Esrange, Sweden. The Earth-to-space uplink
frequency band of 2025-2110 MHz from Inuvik, Canada and Esrange, Sweden will be used
occasionally to upload new firmware to the Myriota payload.

8 Radio Equipment.
8.1 UHF TT&C Transceiver
• NanoComm AX100 UHF Transceiver manufactured by GomSpace.
• Primary transceiver capability for telecommand, telemetry, and schedule uploads.
• The transceiver can operate between 390 MHz and 406 MHz at 9600 bps modulation.
8.1.1 Downlink: UHF Transmit
• Operating Frequency 400.60 MHz
• Output Power: 3 Watts
• EIRP: 3.3 dBW
• Channels: 400.50-400.65 MHz
• Frequency Deviation: 16 kHz
8.1.2 Uplink: UHF Receive
• Operating Frequency 399.95 MHz
• Sensitivity: -110 dBm
• Channels: 399.90-400.05 MHz
• Frequency Stability: ±10 ppm.

Exhibit 2 SpaceQuest PAGE 6

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

8.2 VHF Receiver:
• CERX-145 Narrowband FM Receiver manufactured by SpaceQuest
• Experimental backup VHF Receiver for emergency reboot or satellite power cycle
• 145.92 MHz fixed receive frequency
• GMSK modulation at 9600bps
• Sensitivity: -119 dBm

8.3 S-Band Transceiver:
• GomSpace TR600 S-Band SDR Transceiver
• Primary transceiver for mission data and commands to primary payload
• Space-to-Earth downlink operates in the 2200-2290 MHz frequency band
• Earth-to-space uplink operated in the 2025-2110 MHz frequency band
• 700 Kbps data rate with QPSK modulation
8.3.1 Downlink: S-Band Transmit
• Requested Frequency Band: 1MHz in the 2200-2290 MHz band
• Output Power: 1 Watts
• Peak antenna Gain: 7 dBi
• EIRP: 3.3 dBW
• Data Rate: 700 kbps
• Channels: Antenna Operating Frequency: 2200-2290 MHz
• Necessary Bandwidth: 1,000 kHz
8.3.2 Uplink: S-Band Receive
• Operating Frequency: 1MHz in the 2025-2110 MHz band
• Sensitivity: -100 dBm
• Data Rate: 700 kbps
• Channels: Antenna Operating Frequency: 2015-2110 MHz
• Frequency Stability: ±10 ppm

8.4 UHF Experimental Payload Transceiver
• ERP-100 UHF Transceiver manufactured by SpaceQuest
• UHF transceiver to be used with Myriota’s experimental payload processor
• The transceiver can operate between 390 MHz and 406 MHz at 9600 bps
• Modulation is FM/GMSK
8.4.1 Downlink: UHF Transmit
• Operating Frequency 400.60 MHz
• Output Power: 4 Watts
• EIRP: 4.5 dBW
• Channels: 400.50-400.65 MHz
• Frequency Deviation: 16 kHz

Exhibit 2 SpaceQuest PAGE 7

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

8.4.2 Uplink: UHF Receive
• Operating Frequency 399.95 MHz
• Sensitivity: -112 dBm
• Channels: Tunable SDR
• Frequency Stability: ±10 ppm

A summary of the BRIO Transmitter and Receiver parameters are provided in Figure 4.
Transmitter Transmitter Transmitter Receiver 1 Receiver 2 Receiver 3 Receiver 4
Description 1 2 3
Radio Name UTX SBTX EXTX URX SBRX EXRX VRX
Carrier Frequency, MHz 400.6 ~ 2288.5 400.60 399.95 ~ 2045.5 399.95 145.92
3 dB Bandwidth, MHz 0.015 0.75 0.015 0.015 0.75 0.015 0.015
Necessary Bandwidth, MHz 0.035 1.0 0.035 0.035 1.0 0.035 0.025
20 dB Bandwidth, MHz 0.020 0.80 0.020 NA NA NA NA
60 dB Bandwidth, MHz 0.035 0.90 0.035 NA NA NA NA
Receiver Sensitivity, dBm NA NA NA -110 -100 -112 -119
Antenna Gain, dBi 0.0 7.0 0.0 0.0 7.0 0.0 0.0
Modulation Type GMSK QPSK GMSK GMSK QPSK GMSK GMSK
Total Data Rate (KHz) 9.6 700 9.6 9.6 700 9.6 9.6
Receiver Span (MHz) NA NA NA 0.15 1.0 0.15 0.05
EIRP, dBW 3.3 3.4 4.5 NA NA NA NA
Antenna Polarization Linear Circular Linear Linear Circular Linear Linear

Figure 4 Summary of BRIO Transmitter and Receiver parameters.

9 Antenna Systems
The antenna frequency parameters for the BRIO Satellite are provided in Figure 5.
Lower Upper Freq. Power Output ERP Mean/ Frequency Station
Beam Power
Frequency Frequency Units Units Power/ERP Units Peak Tolerance Class
SBTX 2200 2290 MHz 1.0 W 3.4 dBW Peak +/-10 ppm Mobile

UTX 400.50 400.65 MHz 3.0 W 3.3 dBW Peak +/-10 ppm Mobile

EXTX 400.50 400.65 MHz 4.0 W 4.5 dBW Peak +/-10 ppm Mobile
Figure 5 Antenna Frequency Registration

The antenna emission parameters for the BRIO Satellite are provided in Figure 6.
Lower Upper Modulating Necessary
Beam Units Emission
Frequency Frequency Signal Bandwidth
SBTX 2200 2290 MHz 1M00G1D QPSK 1,000 KHz

UTX 400.50 400.65 MHz 35K0F1D GMSK 35 KHz

EXTX 400.50 400.65 MHz 35K0F1D GMSK 35 KHz
Figure 6 Frequency Emissions Registration

Exhibit 2 SpaceQuest PAGE 8

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

10 Satellite Link Budgets
The UHF TT&C uplink budget is shown in Figure 7. Figure 8 shows the TT&C downlink budget.

Figure 7 Satellite UHF TT&C Uplink Budget

Figure 8 Satellite UHF TT&C Downlink Budget

Exhibit 2 SpaceQuest PAGE 9

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

The S-Band uplink budget is shown in Figure 9. The S-Band downlink budget is Figure 10.

Figure 9 Satellite S-Band Uplink Budget

Figure 10 Satellite S-Band Downlink Budget

Exhibit 2 SpaceQuest PAGE 10

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

The UHF Experimental Payload uplink budget is shown in Figure 11.

Figure 11 Satellite Experimental UHF Uplink Budget
The UHF Experimental Payload downlink budget is shown in Figure 12.

Figure 12 Satellite Experimental UHF Downlink Budget

Exhibit 2 SpaceQuest PAGE 11

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

The VHF uplink budget is shown in Figure 13. The VHF uplink margin is in Figure 14.

Figure 13 Satellite VHF Uplink Budget
VHF Uplink Margin
35

30

25

20
Link Margin (dB)

15 Backup Command Link
145MHz at 9.6 kbps
10 Watts Uplink Power
10 0.0 dBi Sat Antenna Gain
8.0 Grounds Antenna Gain
575 km Altitude
5

0
0 15 30 45 60 75 90
Elevation Angle (Degrees)

Figure 14 Satellite VHF Link Margins Vs. Elevation Angle

Exhibit 2 SpaceQuest PAGE 12

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

The satellite link margins for the UHF TT&C radio are plotted in Figure 15.

UHF Link Margins
35
Down link Margin
30
Uplink Margin
Link Margin (dB)

25

20

15 Command & Telemetry Links
400 MHz at 9.6 kbps
10 10 Watts Uplink Power
3 Watt Sat Transmit Power
0.0 dBi Sat Antenna Gain
5 13.5 Grounds Antenna Gain

0
0 15 30 45 60 75 90
Elevation Angle (Degrees)
Figure 15 Satellite UHF TT&C Link Margins Vs. Elevation Angle

The satellite link margins for the S-Band radio are plotted in Figure 16.

S-Band Link Margins
30
UPLINK MA RGIN (dB)

DOWNLINK MARGIN ( dB)
25
Link Margin (dB)

20

15

Mission Data Links
10 2045 and 2288 MHz at 700 Kbps
10 Watts Uplink Power
1 Watt Sat Transmit Power
7.0 dBi Sat Antenna Gain
5 40 dBi Ground Antenna Gain
575 km Altitude

0
0 15 30 45 60 75 90
Elevation Angle (Degrees)

Figure 16 Satellite S-Band Link Margins Vs. Elevation Angle

Exhibit 2 SpaceQuest PAGE 13

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

The satellite link margins for the UHF Experimental Transceiver is plotted in Figure 17.

Experimental Payload Link Margins
16
Down link Margin
14
Uplink Margin

12
Link Margin (dB)

10

8 Experimental Payload Links
400 MHz at 9.6 kbps
6 3 Watts Uplink Power
4 Watt Sat Transmit Power
4 0.0 dBi Sat Antenna Gain
0.0 Grounds Antenna Gain
2 575 km Altitude

0
0 15 30 45 60 75 90
Elevation Angle (Degrees)
Figure 17 Satellite UHF Experimental Radio Link Margins Vs. Elevation Angle

11 Interference Analysis
11.1 400.50-400.65 MHz (TT&C and Experimental Downlink)
Interference with U.S. federal and commercial assignments in the 400.50-400.65 MHz band
is unlikely as transmissions will only occur while over the SpaceQuest TT&C ground stations.
The 400.50 to 400.65 MHz space-to-Earth band is allocated for UHF Little LEO data services
and has been used experimentally by SpaceQuest for the past 5 years.

11.2 399.90 -400.05 MHz (TT&C and Experimental Uplink)
Interference with U.S. federal and commercial assignments in the 399.00-400.05 MHz band
is unlikely as uplink transmissions will only occur while over the SpaceQuest TT&C ground
stations. The 399.0-400.05 MHz Earth-to-space band is allocated for UHF Little LEO data
services and has been used by SpaceQuest experimentally for the past 5 years.

11.3 2200-2290 MHz (Payload Downlink)
The GomSpaceSR2000 S-Band SDR Transmitter and ANT2000 Antenna is designed to operate
in the 2200-2290 MHz band. In order to avoid interference with the U.S. Federal allocation
in the 2200-2290 MHz band, all S-Band operations will occur outside of the United States.
The nominal S-Band downlink carrier frequency of 2288.5 MHz was selected for analysis for
the BRIO satellite, but only a 1.0 MHz channel in the 2200-2290 MHz band will be used and
coordinated with other authorized users of the band. S-Band downlink operations will occur
several times each day at either Inuvik, Canada or Esrange, Sweden. Transmissions will be
restricted as necessary to eliminate interference with other users of the band.

Exhibit 2 SpaceQuest PAGE 14

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

11.4 2025-2110 MHz (Payload Uplink)
SpaceQuest’s S-Band satellite receiver and antenna system is designed to operate in the
2025-2110 MHz band. The nominal S-Band uplink carrier frequency of 2045.5 MHz was
chosen for analysis for the BRIO satellite, but only a 1.0 MHz channel in the 2025-2110 MHz
band will be used and coordinated with other authorized users of the band.
The 2025-2110 MHz band was chosen for the BRIO experimental license because it is the
only frequency band that can be supported with the chosen S-Band radio equipment – the
GomSpaceSR2000 S-Band SDR Receiver and ANT2000 Antenna. In order to avoid
interference with the U.S. Federal allocation in the 2025-2110 MHz band, all S-Band
operations will occur outside of the United States.
Infrequent S-Band uplink transmissions from Inuvik, Canada or Esrange, Sweden, will be used
to load new firmware to the BRIO satellite and to send confirmations of successful data
packet downloads.

12 Power Flux Density Analysis
12.1 400.50-400.65 MHz (TT&C Downlink)
The Power Flux Density for the UHF TT&C downlink is shown in Figure 18.

UHF Power Flux Density Vs. Elevation Angle
-120
Power Flux Density (dBW/m2/4kHz)

-125

-130

-135
ITU Power Flux Density Limits
Power Flux Density (dBW/m2/4kHz)
-140

-145
0 10 20 30 40 50 60 70 80 90
Elevation Angle (deg)

Figure 18 PFD at the Surface of the Earth for the UHF Transmitter

Exhibit 2 SpaceQuest PAGE 15

FCC Form 442 Exhibit 2 File #: 0220-EX-CN-2018
Technical Information

12.2 2200-2290 MHz (S-Band Downlink)
The PFD for the S-Band downlink satisfies the ITU PFD limits as shown in Figure 19.

S-Band Power Flux Density Vs. Elevation Angle
-140.0

-142.0

-144.0
PFD (dBW/m^2/4 kHz)

-146.0

-148.0

-150.0

-152.0

-154.0 ITU Power Flux Density Limits

-156.0 Power Flux Density (dBW/m2/4kHz)

-158.0

-160.0
0 10 20 30 40 50 60 70 80 90
Elevation Angel (Deg)

Figure 19 PFD at the Surface of the Earth for the S-Band Transmitter

12.3 400.50-400.65 MHz (Experimental Payload Downlink)
The Power Flux Density for the UHF Experimental Payload downlink is shown in Figure 20.

Experimental Payload PDF Vs. Elevation Angle
-120
Power Flux Density (dBW/m2/4kHz)

-125

-130

-135
ITU Power Flux Density Limits

Power Flux Density (dBW/m2/4kHz)
-140

-145
0 10 20 30 40 50 60 70 80 90
Elevation Angle (deg)

Figure 20 PFD at the Surface of the Earth for the UHF Payload Transmitter

Exhibit 2 SpaceQuest PAGE 16

Document Created: 2018-05-09 11:45:05
Document Modified: 2018-05-09 11:45:05

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