Han, Sang-Uk

Kim, Geuk-Nam

Kim, Sanggoo

Kwon, Ki-Ho

Lee, Jungkyu

Lee, Seongwhan

English

DigitalCommons@USU

EEETester: Development of CubeSat platform for space heritage of Korean manufactured Electrical, Electronics, and Electromechanical partKi-Ho Kwon1*, 1Sanggoo Kim1, Jungkyu Lee2, Geuk-Nam Kim2, Seongwhan Lee2, Sang-Uk Han21Korea Aerospace Research Institute, 2NARA Space Technology Inc.AcknowledgmentThis research was supported by  the Korea Aerospace Research Institute Program (L20241537) in 2024.ContactDr. Kiho KwonKorea Aerospace Research InstituteEmail. khkwon@kari.re.kr  System DiagramPDHS interfaces various interface protocol for multi payloadsTCRS and AOCS has redundancy architecture for reliability of the systemBus platform controls the power switch of each payload for efficient system designEEETester subsystem configurationPayload Data Handling System (PDHS) developmentSystem Design Electrical, Electronics, and Electromechanical part Tester (EEETester)Development of CubeSat platform to get the space heritage of Korean manufactured electrical and electronic equipment  To get the space heritage of Korean manufactured EEE part (TRL 6)To expend the ecosystem of space industry using of semi conductor based EEE part for improving reliabilityTo get the space core technology to use KSLV-IIConcept of Operations I. LEOP (Launch & Early Orbit Phase) : Detumbling & early operation II. Mission mode : 100 % duty operation of the payload at sun pointing III. G/S mode : Send the payload data from the payload & SOHIntroduction Parameter EEETester #1 EEETester #2 EEETester #3OrbitAltitude 600 km 500 km 500 kmInc. 97.79° 97.41° 97.41°LTAN/LTDN12:30 10:30 13:30Mission life 12 Months 12 Months 12 MonthsLauncher KSLV-II KSLV-II KSLV-IILaunch date 2025 4Q 2026 4Q 2027 4QPayloadsSamsung MemoryTBD TBDKorean manufactured electronic componentsAD/DA ASIC<Concept of Operations for the EEETester> < EEETester program><EEETester interface diagram> <EEETester power diagram> Use FPGA to Implement for various payload interface for different payload of EEETester #2 & EEETester #3I/F QTY Spec.I2C 2 EA 400k(High Speed Mode)CAN 2 EA 1MSPI 2 EA 1M(Standard), CS 2bitRS232 2 EA 115,200bpsRS422 5 EA 10MbpsLVDS 1 EA 200Mbit/s, 4bit dataSpacewire 1 EA 200Mbit/sVarious Interface for PayloadDesign & AnalysisDevelopment & Test Design the SEE hardness Use SEL detection & Protection circuit SEL protection circuit development<SEL protection IC spec.><Latch-up block diagram>Radiation hardness  Power Sequence analysis Concrete the stable ON/OFF Sequence In-house development of the OBC & PDHS<Power sequence example> <Power sequence analysis for PDHS><Core input power>Power ON/OFF SequenceInput signalInput powerOBC PDHS<SEL protection current graph><IC block diagram>Hardware verification<Functional test of system and memories><PCB design review & signal measurement>Technical development approach To increase reliability to select the COTS components and screening Systemically radiation hardness design & ECC in memories Various interface for muti-interface for different payload users Timing analysis and design for data CMD/TM in space environment<PDHS>Hardware verificationPayload interface test planParameter Spec.FPGA Xilinx SoC (COTS heritage)Memory DDR3L DRAM (8 Gbit)Storage SLC NAND Flash (512 Gbit)Power Consumption 5 W (Average), 11 W (Max)Mass 200 g (TBD)Size 90 x 96 x 12 mm (/w case)Modulation CCSDS CADU format1. Turn on OBC, PDHS, Payload2. OBC control by Ethernet 3. OBC-Payload CMD/TM4. Receiving payload TM5. Transfer payload data to PDHS EEETester SpecificationFSW (Flight Software)6AOCS (Attitude & Orbit Control Subsystem)4Star Tracker & Gryo,Attitudedetermination: < 6/40 arcsec (cross-/along-boresight) Integrated algorithm implementation RW & MTQModular design considering space utilization and structural robustnessPart selection based on mission designSun Sensors & Mag.Use wide-anglesun sensorsUse magnetometer with sun sensorsEPS (Electrical Power Subsystem)2Solar Panels30 % high-efficiency cellsUse doubledeployment solar panels For maximum power generationBattery8S2P configuration172 Wh capacityStorage of generated power and supplyEPSSupply the power to Bus & PayloadOvercurrent & overvoltage protectionTCS (Thermal Control Subsystem)3Thermal control of the heaters for the components susceptible to lower temperatureThermal isolation and passive control with MLISMS (Structure Mechanism Subsystem)112U CubeSatstructureAluminum alloy-based skeleton considering structural robustnessSurface treatment for ground/heat transfer characteristicsKill-switch mechanism for pre-launch External panelsAttachment of panels for securing external components, thermal/space radiation shieldingPDHS (Payload Data Handling Subsystem)7TCRS (Telemetry, Command & Ranging Subsystem)5OBC In-house subsystem with TRL9Use the in-house FSW to control the all of subsystemMain I/F : CAN bus &  RS-422/485 Interface board & harnessExpand interface between subsystem In-house harness with IPC GNSS receiver & antennaConsider GPS signal coverageS-band Transceiver & antennaStable TM/TC configurationUse Omni direction antennaeRedundant configurationX-band transmitter & antennaHigh-speed mission data downloadGSE (Ground Support Equipment)8MGSE12U standard CubeSat test POD Jig for the assembly between payload & bus platformStability MGSE for transportationProtection during storageEGSESimulate bus subsystem signal &  interface with bus platformDynamic simulation of attitude control and sensorsSimulate of solar panel power generationSimulate of Ground station with RF signalSimulate orbit operation scenario during burn-in testControl the multiple payloadsRadiation protection circuitData processing & storage for payload dataCCSDS modulation with CADU In-house FSWOperation mode controlAll subsystem status monitoringOperation TC/TM & Mission data Implement the FDIR8<EGSE configuration>24567< EEETester bus platform>Parameter SpecificationPayloadMass Up to 14 kgSizeUp to 8U( 200 mm x 200 mm x 200 mm)Power 20 W (100 % duty)Power channel3.3V(4ch), 5V(3ch), 12V(3ch), VBAT(1ch)Protocol I/FCAN(1ch), I2C(1ch), RS422(4ch), SpW(1ch), RS232(1ch), SPI(2ch) BusAttitudeControlModeDetumble, Sun pointing, and G/S trackingPointingAccuracy0.05 deg.Off nadir 20 deg.PowerPowerGeneration97.29 WPowerConsumption35.39 W (Inc. Payload 20 W)Battery 186 WhDoD Up to 30 %Comm.S-bandUplinkUp to 256 kbpsS-bandDownlinkUp to 2 MbpsX-bandDownlinkUp to 50 Mbps < Stowed configuration>8UEEE Payload4UBus < Deployment configuration>12U CubeSat Platform

EEETester: Development of CubeSat Platform for Space Heritage of Korean Manufactured Electrical, Electronics, and Electromechanical Part

https://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=6017&context=smallsat

EEETester: Development of CubeSat Platform for Space Heritage of Korean Manufactured Electrical, Electronics, and Electromechanical Part

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