The Evolution of the JPL/NASA Iris Cubesat DSN Compatible
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Jet Propulsion Laboratory The Evolution of the JPL/NASA California Institute of Technology Iris CubeSat DSN Compatible Transponder 8th ESA International Workshop on Tracking, Telemetry and Command Systems for Space Darmstadt, Germany September 25th, 2019 Presenter: Mazen Shihabi Contributors: Courtney Duncan, Michael Kobayashi, and Sarah Holmes Jet Propulsion Laboratory at the California Institute of Technology Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. Jet Propulsion Laboratory Outline California Institute of Technology • History of Iris – V 1.0 (INSPIRE Version) – V 2.0 (MarCO Version) – V 2.1 (Artemis -1 “formerly EM-1” Version) • Design, Specifications, Modes and Performance – Hardware, Firmware, and Software – Manufacturing and Testing – Modes – Performance: Downlink, Uplink, SSPA and LNA • Missions used/using Iris – INSPIRE, MarCOs & Artemis-1 (formerly EM-1) • Additional Features being Infused and Future Enhancements Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 2 Jet Propulsion Laboratory What is in the name Iris (Iρις) California Institute of Technology • Not an acronym • Iris – a goddess associated with communication, messages, the rainbow and new endeavors • “Little Sister” to Electra – Electra is a JPL SDR UHF Relay Radio. • Cousin of Cassandra (Cassy) The Iris: an Illuminated Souvenir (1852), upload.wikimedia.org/wikipedia/commons/4/49/1852_Iri – Ground Support Equipment (GSE) s_Illuminated_Souvenir.png. Public Domain that is used for testing Iris 3 Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. Jet Propulsion Laboratory Iris Transponder Evolution History California Institute of Technology • Iris V1.0: To extend CubeSat/SmallSat 10.1 x 10.1 x 4.5 cm deep space capability, JPL introduced the Interplanetary NanoSpacecraft Pathfinder In Relevant Environment (INSPIRE) mission1, coupled with the first-generation of Iris deep-space Iris V1.0 Stack transponder2. 10.1 x 10.1 x 7.5 cm • Iris V2.0: The radio was further developed, matured, and in 2018 successfully flown onboard Mars Cube One (MarCO), to support InSiGht’s Iris V2.0 Stack Mars Entry, Descent, and LandinG 10.1 x 10.1 x 5.6 cm (EDL)3. • Iris V2.1: The latest version of Iris includes design updates that support Iris V2.1 Key Specifications4 4 Artemis-1 CubeSats missions . Iris V2.1 Stack 1 A. Klesh et al., “INSPIRE: Interplanetary NanoSpacecraft Pathfinder In Relevant Environment,” in AIAA SPACE Conf. and Expo., San Diego, CA, 2013. 2 C. B. Duncan et al., “Iris Transponder – Communications and Navigation for Deep Space”, in Small Satellite Conf., Logan, UT, 2014. 3 A. Klesh et al., “MarCO: Early Operations of the First CubeSats to Mars,” in Small Satellite Conf., Logan, UT, 2018. 4 M. M. Kobayashi et al., “Iris Deep-Space Transponder for SLS EM-1 CubeSat Secondary Payloads”, IEEE Aerospace and Electronic Systems Magazine, Volume 34, Issue 9, pp 34-44, September 1, 2019. Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 4 Jet Propulsion Laboratory INSPIRE Iris (V 1.0) California Institute of Technology Stack of Boards – Modular Design • 10.1 x 10.1 x 4.5 cm CubeSat Paradigm = 0.46U DSN – Compatible X-band Transponder • 0.45kg, 13 W DC 10.1 x 10.1 x 4.5 cm (Tx/Rx), 0.2 W RF output • 4 slices: – Digital: Virtex-5 Marina-2 FPGA (no sequential Modem Processor processor) Virtex 5 Power Supply Board – Power Board – X-Band Exciter X-Band Receiver – X-Band Receiver X-Band Exciter 23 dBm – 1 MHz SPI Iris Prototype Stack (~2013) InterFace 5 Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. Jet Propulsion Laboratory MarCO Iris (V 2.0) California Institute of Technology • 10.1 x 10.1 x 7.5 cm = 0.77U: • 1.2kg, 35W DC (Tx/Rx), 4W RF output • Five slices: – Digital: Virtex-6 (Industrial-grade) with embedded CPU (LEON3-FT softcore) 10.1 x 10.1 x 7.5 cm – Power – X-Band Exciter – X-Band Receiver – UHF Receiver – 1 MHz SPI Interface • Radiation Tolerance: 15 krads TID – radiation requirement was 2.9 krads for the 9-month cruise to Mars. • 15-month initial development cycle Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 6 Jet Propulsion Laboratory Artemis-1 Iris (V2.1) California Institute of Technology • Radio: 10.1 x 10.1 x 5.6 cm = 0.57 U • 0.86 kg, 34 W DC (Tx/Rx), 4W RF output • Four slices: • Digital: Virtex 6 (Defense-grade) with embedded CPU (SPARC V8: DIGITAL LEON3-FT softcore) running at 50 TRIPLE MHz SSPA POWER • Power Supply Board DUAL 5.6 • Exciter cm EXCITER LNA 10.1 cm • Receiver • 1 MHz SPI Interface RECEIVER • 2-ch LNA: 7 x 4.8 x 1.3 = 44 cc 10.1 cm • 3-ch SSPA: 8.7 x 4.3 x 1.8 = 68 cc • Receiver Noise Figure: 3.5 dB • 62.5 bps to 4 Mbps, CCSDS Deep Space • Doppler, Seq. Ranging, PN Regen, PN Delta DOR • Radiation Tolerance: 23 krads TID • Licensed to Space Dynamics Laboratory (SDL) for manufacturing and sale (POC: [email protected]) Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 7 Jet Propulsion Laboratory Iris Generational Specification SummaryCalifornia Institute of Technology Iris Specification Units Iris V1.0 Iris V2.0 Iris V2.1 INSPIRE Version MarCO Version Artemis-1 Version Xilinx Virtex-5 Xilinx Virtex-6 Xilinx Virtex-6 Digital Processor (commercial-grade) (Industrial-grade) (defense-grade) SPARC-Based SPARC-Based Embedded CPU N/A Leon3-FT Softcore Leon3-FT Softcore No. Of Slices 4 5 4 Mass (excl. SSPA/LNA) grams 450 1200 860 Volume (excl. SSPA/LNA) U 0.46 0.77 0.56 32 Mbit NOR-Flash 32 Mbit NOR-Flash 32 Mbit NOR-Flash Memory 128 Mbit Phase-Change Memory chip 16 Mbit SRAM 16 Mbit SRAM for the SPI interface 4 Mbit EDAC SRAM 4 Mbit EDAC SRAM S/C Interface 1 MHz SPI± 1 MHz SPI 1 MHz SPI Bus Power Interface Vdc 6.4 - 8.4 10.5 – 12.3 9.0 – 28.0 DC Power W 13.0 30.0 (including 5-W SSPA) 30.0 (including 5-W SSPA) RF Output Power W 1.0§ 5.0 5.0 Receiver Noise Figure dB 5.0 – 6.0 3.5 3.5 Receiver Sensitivity dBm -135 @ 70 Hz LBW -139 @ 70 Hz LBW -151 @ 20 Hz LBW Downlink Frequencies MHz 8400 - 8500 8400 - 8500 8400 - 8500 Uplink Frequencies MHz 7145 - 7235 7145 - 7235 7145 - 7235 Turn-around Ratio 880/749 880/749 880/749 Uplink Date Rates bps 1,000 62.5 & 1,000 62.5 - 8,000 Downlink Data Rates bps 62.5 - 64,000 62.5 & 1,000 & 8,000 62.5 - 256,000 UHF Receive Freq MHz N/A 390 - 405 N/A UHF Rertun Link Rate bps N/A 8,000 N/A PCM/PSK/PM w/ subcarrier PCM/PSK/PM w/ subcarrier PCM/PSK/PM w/ subcarrier Modulations Waveforms PCM/PM w/ biphase-L, BPSK PCM/PM w/ biphase-L, BPSK PCM/PM w/ biphase-L, BPSK Conv & Reed Solomon Telemetry Encoding Conv & Reed Solomon Turbo 1/6 Turbo ½, 1/3, 1/6 Navigational Support Doppler, SR* Doppler, SR, DDOR† Doppler, SR, DDOR Radiation Tolerance krads N/A 15.0 TID‡ 23.0 TID ±SPI: Serial Peripheral Interface bus †DDOR: Delta Differential One-way Ranging § For the INSPIRE mission, the PA was backed off to 0.2 W to save power ‡TID: Total Ionizing Dose * SR: Sequential Ranging Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 8 Jet Propulsion Laboratory High Level Hardware Overview California Institute of Technology Iris LNA Modular MIC assembly Iris Transponder Stack • Reduce noise figure by shortening cable Digital Processor length from antenna Xilinx Virtex-6 FPGA • Separate gain cavities Leon3FT Softcore SRAM between LNA and Rx 50MHz Processor TCXO (risk of oscillations) U/L DATA RX PLO Command 50 MHz AGC X-Band LNA Decoder Tracking X-Band Uplink VVA ADC X- Loops D/L DATA 71457145 ––72357235 MHz MHzk Pre-Select Image SAW Filter X-130-130dBmdBm toto -70 -70dBm dBmk Reject X-band Receiver I-DAC Iris SSPA X-Band SSPA X-Band Exciter DDS DDS Telemetry X BandX-X Downlink DAC Generator Modulator 8400 –- -8500 MHz Isolator TX PLO DDS Input 3.8 4 W BOL Filter Modular MIC assembly Q-DAC • Provide superior heat dissipation path to Modular stacked-slice assembly structure/radiator • Chip-and-wire assy to • Superheterodyne receiver with single-downconversion stage to 112.5 MHz IF reduce losses for • Digitally closed tracking loops (carrier, subcarrier, symbol) higher efficiency • Direct Digital Synthesis (DDS) reference for downlink carrier Doppler tracking • Baseband telemetry modulated direct at X-band • Embedded softcore processor (Leon3-FT) for configuration and protocol mgmt Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 9 Jet Propulsion Laboratory Iris Hardware Photos California Institute of Technology DiGital Processor (RaDix) Power Supply Board DDS Virtex-6 DAC Flyback FPGA Conv 1V SRAM ReG FLASH Switchers X-band Exciter X-band Receiver Tx-Out IF I/Q Amps Mixer Rx-PLL SAW ImG-Rej Filters Mixer VVAs TCXO Tx-PLL Rx-In Copyright ©2019 California Institute of Technology. Government Sponsorship Acknowledged. 10 Jet Propulsion Laboratory Software Specs / Architecture California Institute of Technology • Single-threaded Internal • SPARC V8 instruction set (same as used on Interrupt UST1) Reset SRAM EDAC Error – UST stands for the Universal Space Transponder Handler which is the next Generation SDR JPL INIT transponder that can support simultaneous CDH Peek multiband operations with data rates up to 37.5 Cmd Handler Mbps RX and 300 Mbps TX. Execute C&DH CMD – This allows a sinGle radio to support all the DMA Complete direct-to-Earth and relay communication Handler DMA requirements for even complex mission N DONE / scenarios, reducinG the total cost, mass, and READ power.