HSAT Experiment Narrative v3

0016-EX-CN-2016 Text Documents

Harris Corporation

2016-12-01ELS_185034

HSAT-1 Exhibit 1: Experiment Description Document for FCC Application Stephen T. Gillespie, P.E. Harris Corporation Revision B 05 August 2016 Revised 01 December 2016 NON-EXPORT CONTROLLED INFORMATION

TABLE OF CONTENTS 1.0 INTRODUCTION .............................................................................................................................. 3 2.0 TECHNICAL DETAILS ........................................................................................................................ 4 2.1 PHYSICAL DESCRIPTION AND EXPERIMENT .................................................................................................. 4 2.2 RADIO FREQUENCY SPECTRUM UTILIZED .................................................................................................... 5 2.2.1 Requested Emitter Frequency Allocations .............................................................................. 6 2.3 ANTENNA DETAILS ................................................................................................................................ 6 2.3.1 Space Segment Emitting Antennas ......................................................................................... 6 2.3.2 Space Segment Receive-Only Antennas .................................................................................. 9 2.3.3 HSAT-1 Ground Terminal Antenna ........................................................................................ 13 2.4 HARRIS “STOP BUZZER” CONTACT.......................................................................................................... 14 Table of Figures Figure 2-1: HSAT-1 Physical Description ......................................................................................................... 4 Figure 2-2: Globalstar GAT-17PP Tx Antenna Pattern ................................................................................... 6 Figure 2-3: Globalstar GAT-17PP Rx Antenna Pattern .................................................................................... 7 Figure 2-4: Globalstar GAT-17PP Antenna .................................................................................................... 7 Figure 2-5: Measured S-band Patch Azimuth Pattern .................................................................................... 8 Figure 2-6: Measured S-band Patch Elevation Pattern ................................................................................... 9 Figure 2-7: AIS Monopole Antenna Directivity ............................................................................................. 10 Figure 2-8: BBDA Directivity, 159.0125 MHz ............................................................................................... 11 Figure 2-9: BBDA Directivity, 195 MHz ........................................................................................................ 11 Figure 2-10: BBDA Directivity, 397.5 MHz ................................................................................................... 12 Figure 2-11: BBDA Directivity, 1260 MHz .................................................................................................... 12 Figure 2-12: Predicted HSAT-1 Ground Terminal Antenna Pattern (not including radome loss) ................ 13 Figure 2-13: HSAT-1 Ground Terminal Location & Facility Details............................................................... 14 Table of Tables Table 2-1: HSAT-1 Technical Description ....................................................................................................... 4 Table 2-2: Radio Frequency Spectrum Summary for HSAT-1 ........................................................................ 15 NON-EXPORT CONTROLLED INFORMATION Page 2 of 15 Revision B (01 Dec 2016)

1.0 Introduction Harris Corporation is requesting a 24 month experimental license from the Federal Communication Commission’s (FCC) Office of Engineering and Technology (OET) in order to complete the objectives of the HSAT-1 mission. The HSAT-1 cubesat is an orbital experimental testbed being developed by Harris Corporation for launch in Q2 2017. The following objectives of the HSAT-1 orbital experiment will improve the radio state-of-the-art: • Assess the effectiveness of radiation mitigation techniques of the payload in the actual environment with continual performance and event monitoring • Assess the performance of a broad-bandwidth deployable antenna (BBDA) specifically designed for cubesats through on-orbit measurement • Assess the effective coverage of Harris’ earth-to-space and space-to-earth Tracking, Telemetry, and Control (TT&C) and payload experiment data communications through on-orbit demonstration of an S-band radio In order to assess payload performance in a radiation environment, the HSAT-1 orbital testbed must continually receive and process, which requires a signal-rich environment. Initially, HSAT-1 will receive and process maritime Automatic Identification System (AIS) signals using a TRL-9 commercially available cubesat antenna, hereafter referred to as the “AIS monopole antenna”. TT&C and payload experiment data communications will be performed during the first phase through the Globalstar constellation & network. Approximately 60 days after launch, HSAT-1 will disable the AIS monopole antenna and deploy a broad-bandwidth deployable antenna (hereafter referred to as the “BBDA”). This begins the second phase of the payload experiment. The payload will receive VHF broadcast signals in addition to AIS signals to determine the low band performance. Solar noise will also be received to determine performance of the BBDA’s mid and upper band. During this time, TT&C and payload experiment data communications through the S-band radio to a Harris ground terminal will be demonstrated. Since the BBDA receives in a much wider bandwidth, a higher data rate modem than the Globalstar is required to transmit the payload experiment data to satisfactorily characterize the performance of the antenna. The S-band radio meets this need with a higher data rate downlink capability. Specific frequency bands requested are listed in Section 2.2. Usage of the requested RF spectrum for this flight experiment is critical to the success of the flight experiment. The requested RF communications implementation provides both the ability to successfully command the spacecraft and the ability to receive critical engineering telemetry and experiment data. Harris Corporation is requesting a 24 month experimental license from the Federal Communication Commission’s (FCC) Office of Engineering and Technology (OET) in order to complete the objectives of the HSAT-1 mission. Harris Corporation will be the sole owner and operator of the HSAT-1 satellite. NON-EXPORT CONTROLLED INFORMATION Page 3 of 15 Revision B (01 Dec 2016)

2.0 Technical Details 2.1 Physical Description and Experiment The HSAT-1 orbital testbed is a 6U cubesat with two deployable solar array panels and two deployable antennas as depicted in Figure 2-1. Harris Corporation has signed a Launch Services Agreement (LSA) with Spaceflight, Inc, to launch HSAT-1 on an Indian Polar Satellite Launch Vehicle (PSLV) in May 2017 through the Indian Space Research Organization (ISRO) at the SHAR (Sriharikota) Spaceport (Satish Dhawan Space Center). The satellite will fly in a sun-synchronous orbit at 500 km altitude, 97.4° inclination, and 9:30 AM Local Time Descending Node (LTDN). Table 2-1 details other technical parameters of HSAT-1. Figure 2-1: HSAT-1 Physical Description Table 2-1: HSAT-1 Technical Description Parameter Value / Description Mission Life 2 years minimum Mass < 13.2 kg Size 6U Propulsion None Attitude Control Reaction wheels & torque rods Batteries Nine 2.8 amp-hour lithium ion cells Primary TT&C Link Globalstar Network Redundant TT&C Link S-band Radio NON-EXPORT CONTROLLED INFORMATION Page 4 of 15 Revision B (01 Dec 2016)

HSAT-1 will be launched in a powered off state within its dispenser. Upon orbital insertion, HSAT-1 will be ejected from its dispenser and begin a power-on and boot sequence followed by orientation into a sun-safe mode (solar panels oriented towards sun). No radio communications will occur for a minimum of 30 minutes after ejection from the launch dispenser. After the radio blackout period has ended, the satellite will transmit state-of-health telemetry to Harris through the Globalstar constellation and network using Globalstar’s GSP-1720 modem. Once the data has been reviewed, Harris will command the satellite to deploy the AIS monopole antenna. This antenna is manufactured by Innovative Solutions in Space and is fully qualified with flight history (TRL-9). The AIS monopole antenna is fed to a Harris-manufactured AIS receiver, which has qualification-by-similarity history. Once deployed, Harris will upload specific mission decks that will command the payload to begin receiving and processing AIS signals. Telemetry will be recorded indicating specific payload performance as well as any radiation-induced events. During this time the telemetry and corresponding mission data will be communicated to the Harris Satellite Operations Center (HSOC) through the Globalstar network. After the primary payload objectives have been demonstrated (up to 2 months after launch), Harris will command the satellite to deploy the BBDA. Once deployed, Harris will review the deployment telemetry and then switch the payload receiver from the AIS monopole antenna to the BBDA. Payload processing will continue as before, but now utilizing four separate bands over the BBDA range instead of one. This presents the opportunity to continue to monitor payload performance and radiation effects over mission life while utilizing several discrete regions across the BBDA to evaluate specific antenna performance Testing will conclude 24 months after launch, at which time the spacecraft will be passivated and decommissioned. Deorbit will occur naturally through atmospheric drag. Based on an analysis utilizing NASA’s DAS 2.0.2 software with specific HSAT-1 inputs (mass, size, form, initial orbit, material types, etc), HSAT-1 is anticipated to remain in orbit less than 4.3 years total. In addition, the HSAT-1 design passed all other requirements of debris and deorbit in accordance with NPR 8715.6A, which addresses breakups and other debris-producing events. Reference Exhibit 2 Document 7052742 for the complete Orbital Debris and Deorbit Assessment. 2.2 Radio Frequency Spectrum Utilized Table 2-2 summarizes the requested radio frequency spectrum for the HSAT-1 satellite. These bands were selected for various reasons: 1) Reducing cost through high reuse and utilization of existing designs (the hardware has been previously designed for these frequencies and some long lead components were already available in inventory); 2) Four separate bands spaced over the BBDA design band is necessary for evaluating antenna performance; These bands already contain an abundance of continuous signals such as AIS and VHF broadcasting which allow the payload to continually receive and process in order to monitor and detect radiation events. NON-EXPORT CONTROLLED INFORMATION Page 5 of 15 Revision B (01 Dec 2016)

2.2.1 Requested Emitter Frequency Allocations Harris Corporation specifically requests to utilize the following allocations for the HSAT-1 satellite system:  Two emitters on the HSAT-1 mobile satellite o Globalstar: Space-to-space (1610-1626.5 MHz) o Downlink: Space-to-earth (2180-2185 MHz)  One ground terminal owned by Harris Corporation o Uplink: Earth-to-space (2005-2006.25 MHz) Harris Corporation requests the above specific frequency allocations to meet the current ground terminal design capabilities, there is flexibility to modify the request to nearby bands in case of coordination issues with other users. 2.3 Antenna Details 2.3.1 Space Segment Emitting Antennas 2.3.1.1 Globalstar Patch Antenna HSAT-1 initial and primary TT&C and payload experiment communications link is through the Globalstar GAT-17PP patch antenna in conjunction with the Globalstar GSP-1720 modem aboard the satellite. The transmit element provides +4.5 dBic gain within the operating frequency band of 1610-1626.5 MHz. The receive element provides +0.2 dBic gain at 2483.5-2500.0 MHz. Figure 2-2 details the radiating pattern of the patch antenna for transmit, and Figure 2-3 details the pattern for receive. Figure 2-2: Globalstar GAT-17PP Tx Antenna Pattern NON-EXPORT CONTROLLED INFORMATION Page 6 of 15 Revision B (01 Dec 2016)

Figure 2-3: Globalstar GAT-17PP Rx Antenna Pattern Figure 2-4: Globalstar GAT-17PP Antenna 2.3.1.2 S-band Passive Patch Antenna HSAT-1 secondary TT&C and payload experiment communications link is through a custom passive patch antenna in conjunction with a Tethers Unlimited S-band radio aboard the satellite. This patch antenna will transmit signals containing TT&C and payload experiment data to the Harris Ground Terminal at 2180-2185 MHz. Figure 2-6 details the radiating pattern of the antenna at the center of the requested band. NON-EXPORT CONTROLLED INFORMATION Page 7 of 15 Revision B (01 Dec 2016)

Figure 2-5: Measured S-band Patch Azimuth Pattern NON-EXPORT CONTROLLED INFORMATION Page 8 of 15 Revision B (01 Dec 2016)

Figure 2-6: Measured S-band Patch Elevation Pattern 2.3.2 Space Segment Receive-Only Antennas 2.3.2.1 S-band Receive Patch Antenna HSAT-1 will utilize a custom passive patch antenna in conjunction with a Tethers Unlimited S-band radio aboard the satellite. This antenna is separate from the patch antenna described in Section 2.3.1.2, and will receive TT&C signals from the Harris Ground Terminal at 2005-2006.25 MHz. The patch antenna receive pattern is identical to the radiating pattern depicted in Figure 2-6. 2.3.2.2 Payload AIS Monopole Antenna HSAT-1 will utilize a deployable monopole whip antenna manufactured by Innovative Solutions in Space to receive AIS signals as part of the payload experiment. The antenna will receive AIS signals between 159.0125-161.025 MHz. Figure 2-7 details the pattern of the antenna at 159.0125 MHz. NON-EXPORT CONTROLLED INFORMATION Page 9 of 15 Revision B (01 Dec 2016)

Figure 2-7: AIS Monopole Antenna Directivity 2.3.2.3 Payload Broad Bandwidth Deployable Antenna (BBDA) HSAT-1 will utilize a custom broad bandwidth deployable antenna (BBDA) manufactured by Harris Corporation which will receive various AIS, broadcasting, and noise from 159.0125-1260.0 MHz as a part of the payload experiment. Figure 2-8, Figure 2-10, and Figure 2-11 detail the pattern of the BBDA at 159.0125 MHz, 195 MHz, 397.5 MHz, and 1260.0 MHz respectively. Specific frequency bands of the receiver are outlined in Table 2-2. Successful demonstration of this antenna technology will improve the state of the art for cubesat wideband deployable antennas. NON-EXPORT CONTROLLED INFORMATION Page 10 of 15 Revision B (01 Dec 2016)

Figure 2-8: BBDA Directivity, 159.0125 MHz Figure 2-9: BBDA Directivity, 195 MHz NON-EXPORT CONTROLLED INFORMATION Page 11 of 15 Revision B (01 Dec 2016)

Figure 2-10: BBDA Directivity, 397.5 MHz Figure 2-11: BBDA Directivity, 1260 MHz NON-EXPORT CONTROLLED INFORMATION Page 12 of 15 Revision B (01 Dec 2016)

2.3.3 HSAT-1 Ground Terminal Antenna HSAT-1’s secondary TT&C communications uplink (the Globalstar Radio being the primary) will utilize a 4.2 meter parabolic dish antenna located at 28.026552, -80.604989 (Lat, Lon NAD83) on a rootop antenna test platform of a Harris Corporation facility in Palm Bay FL to send TT&C to the HSAT-1 spacecraft. The location and elevation of the proposed ground terminal is shown in Figure 2-13. This antenna will provide 35.1 dBic transmit gain (including radome loss) within the operating frequency band of 2005- 2006.25 MHz, with 2.5° half-power beamwidth. Figure 2-12 details the radiating pattern of the antenna. No other ground stations will communicate directly with HSAT-1. This antenna will also receive TT&C and payload experiment data transmitted by the satellite at 2180-2185 MHz. Figure 2-12: Predicted HSAT-1 Ground Terminal Antenna Pattern (not including radome loss) NON-EXPORT CONTROLLED INFORMATION Page 13 of 15 Revision B (01 Dec 2016)

Figure 2-13: HSAT-1 Ground Terminal Location & Facility Details 2.4 Harris “Stop Buzzer” Contact Thomas Low, Ground Segment Architect tlow03@harris.com Harris Corporation SIS, Palm Bay FL 321-729-2899 NON-EXPORT CONTROLLED INFORMATION Page 14 of 15 Revision B (01 Dec 2016)

Table 2-2: Radio Frequency Spectrum Summary for HSAT-1 Modem / Active Band Type Location Function Description Antenna Type ERP (W) Polarization Modulation Waveform & Coding Receiver (MHz) HSAT-1 Comm Downlink Globalstar Satellite GSP-1720 GAT-17PP Patch 0.76 1610-1626.5 LHCP QPSK/CDMA Reference Globalstar Default/Primary Space-to-space (Mobile Sat) Rolloff factor 0.25, Reed- HSAT-1 Tethers Comm Downlink S-Band Solomon 255/239 Emitters Satellite Secondary Space-to-Earth Unlimited Passive Patch 5.72 2180-2185 LHCP 8PSK 7-7/8 CC (Mobile Sat) Swift-SLX 5 MHz Occupied BW Rolloff factor 0.25, 7-1/2 Melbourne, FL Harris Ground S-Band Harris Parabolic Reflector 312.01 2005-2006.25 RHCP Offset QPSK CC (Fixed) Terminal (Uplink) Earth-to-space 1.25 MHz Occupied BW HSAT-1 L1 NovAtel Satellite GPS Passive Patch 1575.42 RHCP GPS L1 waveform, C/A coding Space-to-Space OEM615 GPS (Mobile Sat) HSAT-1 Comm Uplink Globalstar Satellite GSP-1720 GAT-17PP Patch 2483.5-2500 LHCP QPSK/CDMA Ref Globalstar Default/Primary Space-to-Space (Mobile Sat) HSAT-1 Tethers Rolloff factor 0.25, 7-1/2 Comm Uplink S-Band Satellite Unlimited Passive Patch 2005-2006.25 RHCP Offset QPSK CC; 1.25 MHz Occupied Secondary Earth-to-Space (Mobile Sat) Swift-SLX BW Harris Ground Rolloff factor 0.25, Reed- Receivers Melbourne, FL S-Band 4.2m Parabolic NA Terminal Harris 2180-2185 LHCP 8PSK Solomon 255/239, 7-7/8 (Fixed) Space-to-Earth Reflector (Downlink) CC; 5 MHz Occupied BW HSAT-1 AIS signal AIS Monopole Satellite AIS "Channel A" 155.98-162.10 Linear AIS waveform receiver Antenna (Mobile Sat) Harris Corp PN 3266638- Broad Band 155.98-162.10 HSAT-1 101 Deployable VHF/UHF/L- 174-216 Satellite UHF "Channel B" Antenna Linear AIS, VHF Broadcast, Solar noise band receiver 385-410 (Mobile Sat) Harris Corp 1220-1300 3266643-101 NON-EXPORT CONTROLLED INFORMATION Page 15 of 15 Revision B (01 Dec 2016)


Document Created: 2016-12-01 12:58:29
Document Modified: 2016-12-01 12:58:29
© 2025 FCC.report
This site is not affiliated with or endorsed by the FCC