KARI - Korea Aerospace Research institute

Localization of low-cost, high-efficiency core components to enhance competitiveness of small satellite launch vehicles

• 
  Common Bulkhead Propellant Tank

  • A lightweight, low-cost tank using a common bulkhead structure for upper stages of small launch vehicles, developed using an Al-Li high-performance alloy, friction stir welding, and domestic cryogenic insulation technology
  • The upper core component of a 500 kg class satellite (500 kilometers in geosynchronous orbit) small launch vehicle system.

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  SPPO 첫 완성 기술, 정지궤도 위성용 GNSS 수신기: Items, Development Goals에 대한 표 입니다.

  Items	Development Goals
  Size	2.0 ± 0.2m(D) x 3.0 ±0.5m(L)
  Weight	260 kg or less

• 
  Low-Cost, Lightweight Launch Vehicle Avionics

  • A modular, integrated avionics system enabling mission control, power management, engine/TVC control, telemetry, and emergency shutdown for small launch vehicles, optimized for reduced cost, size, and weight
  • Development of ground performance validation equipment for performance verification of the entire scenario from launch preparation to mission completion of the small launch vehicle Aeonix
• 
  Stage-to-Stage Umbilical Connector

  • Development of a qualified (QM) umbilical model that supports fuel/oxidizer (liquid methane, kerosene, LOX), gases (ambient, high-pressure, cryogenic), and electrical connections for small launch vehicles
  • Identification of technical conditions to ensure that the electrical supply, propellant/gas charging, and depressurization processes during the ground operation of the small launch vehicle meet operational conditions
  • Umbilical separation technology for small launch vehicles during launch and stage separation, and technology to ensure structural integrity under flight loads
  • Design of umbilical ground interface technology for efficient operation of umbilicals connected between stages of a small launch vehicle

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  단간 연결 엄빌리칼: Items, Specification에 대한 표 입니다.

  Items	Development Goals
  Type and operating flow of propellant gas	Liquefied Methane(LCH4) Kerosene Liquefied Oxygen(LOX) Air, GN2, GHe
  	Operating flow rate of LCH4, LOX : 530LPM Operating flow rate of Kerosene : 320LPM

Strengthening domestic capabilities in nationally prioritized space technologies and reducing foreign dependency by securing key payload technologies for Earth observation and communication missions

• 
  Electro-Optical Payload Actuation Unit

  • Development of an actuator system for next-generation GEO ocean observation payloads (GOCI)
  • Derive/analyze/validate the orientation model through BM/QM manufacturing/environmental/performance testing of the on-arm (OAM) and EM/QM manufacturing/environmental/performance testing of the two-axis (TAM)

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  전자광학 탑재체용 구동부: Items, Specification에 대한 표 입니다.

  Items		Specification
  OAM (One Axis Mechanism)	Pointing accuracy	< 0.2 deg
  	Angular velocity	> 24deg/s
  TAM (Two Axes Mechanism)	Pointing accuracy	< 0.006 deg
  	Angular velocity	> 1deg/s
  	Pointing stability	< 4urad/100s

• 
  2D Multichannel Infrared Detector

  • Localization of a multichannel infrared detector (mid-IR and far-IR bands) using T2SL technology for both GEO and LEO Earth observation satellites
  • Development of domestic technology for high sensitivity/large area infrared detector, a core component of satellite payload module

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  2차원 다채널 적외선 검출기: Items, Specification에 대한 표 입니다.

  Items	Specification
  	2-D multi-band MWIR detector	2-D multi-band LWIR detector
  Wavelength	3 ~ 5.3𝝁𝚖	10 ~ 12.5𝝁𝚖
  Format/Pixel pitch	2048 x 2048 / 10𝝁𝚖	1024 x 1024𝝁𝚖
  NETD	≤ 25mK(@80K)	≤ 35mK(@65K)

• 
  Ka-Band Transmitter and Active Phased Array Antenna

  • High-performance, compact, and lightweight Ka-band antenna and transmitter system featuring electrical beam steering and software-defined radio technology, designed for practical satellite downlink systems
  • System optimization through single unit modularization of Ka band transmitter and Ka band active array antenna
  • Core components of satellite payload PDTS (Payload Data Transmission Subsytem), which requires high-speed data transmission of 4 Gbps or more

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  Ka밴드 송신기 및 Ka밴드 능동형 어레이 안테나: Items, Specification에 대한 표 입니다.

  Items	Specification
  Frequency	25.2 GHz ~ 27 GHz
  Beam steering range	Az : -60⁰ to 60⁰, El : -60⁰ to 60⁰
  Transmission speed	≥ 4Gbps(2 Channels)

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  Code/Message Generator for Navigation Satellites

  • Leading-edge navigation code and message generator for inclusion in the Korean satellite navigation system
  • This system generates navigation codes and messages based on navigation and correction data received from the ground to provide ultra-precise PNT services
  • This task was designed to be applied to the KPS project and was developed to be suitable for the Korean navigation satellite in consideration of system linkage

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  항법위성용 코드/메세지 생성기: Items, Specification에 대한 표 입니다.

  Items	Specification
  Chipping Rate	Al least 1.023Mchip/s
  Data Rate(Sample Rate)	At least 50SPS

Enhancing localization of core bus technologies and global competitiveness by developing high-precision attitude control and GEO satellite subsystems

• 
  Storable Bipropellant Thruster

  • Development of a thruster system using MMH fuel and an NTO oxidizer for application in GEO satellites, lunar landers, and deep space exploration missions

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  저장성 이원추진제 추력기: Items, Specification에 대한 표 입니다.

  Items	Specification
  Specific Impulse	287s
  Nominal Thrust	10N

• 
  200mN-Class High-Thrust Electric Propulsion System:

  • Development of a Hall thruster capable of producing thrust exceeding 200 mN for GEO satellites in the 3-ton class, along with a 5kW high-voltage power processing unit (Qualification Model)
  • Establish a test facility for large-scale electric propulsion system of several kW and conduct performance/lifetime test
  • Development of life analysis modeling for computational analysis to compensate for the limitations of experimental approach to Hall thruster plasma
  • Successful execution of this project will secure the technology for applying all-electric propulsion systems to Korea's next-generation geostationary satellites and deep space probes

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  200mN급 고추력 전기추진시스템: Items, Specification에 대한 표 입니다.

  Items	Specification
  Nominal Thrust	200mN
  Specific Impulse	≥ 1,500s
  Total Impulse	1.25MNs
  Efficiency	50%
  Output Power	5kW / Max. 350VDC
  Lift Time	≥ 1236hr
  Fuel	Xenon

• 
  Control Moment Gyro for High-Mobility Satellites

  • The CMG is a core component of the attitude control system for LEO satellites, enabling high-speed, agile orientation changes
  • A key technology for high-speed, high-motion attitude conversion of satellites that can generate control torque dozens of times larger than the reaction wheel mounting method
  • Developed a Control Moment Gyro Assembly (CMA) consisting of four CMGs for satellite attitude control for the next generation of medium-class utility satellites

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  고속 고기동 위성의 제어모멘트자이로: Items, Specification에 대한 표 입니다.

  Items	Specification
  Torque	Max. 30N-m
  Angular Momentum	Max. 15N-m-s
  Gimbal Rate	Max. 2rad/s
  Weight	Total 95kg

• 
  Practical-Class Multi-Head Star Tracker

  • Improves upon single-head star trackers by enhancing dynamic performance and attitude accuracy in off-axis conditions
  • Satisfied the orientation precision performance required by domestically developed satellite systems such as multi-purpose utility satellites and clairvoyant satellites

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  실용급 위성 다중 광학머리 별추적기: Items, Specification에 대한 표 입니다.

  Items	Specification
  Configuration	3 Optical Head(OH) / Fully Redundant Electronic Unit(EU)
  Accurancy(@ 3OH)	Pixel Spatial Error : < 3.3 arcsec(3𝛔, 3axes) NEA : <1.0 arcsec / √Hz(3𝛔, 3axes)
  Update Rate	Max. 30Hz
  Slew Rate	Acquisition from Lost in Space : Max. 10⁰ / sec / Tracking : Max. 10⁰ / sec / Full Performance : Max. 1⁰/sec
  Mass	1 OH < 1.8kg(including Baffle) / EU < 3.5kg(fully redundant)
  Size	1 OH < 132mm x 160mm x 297mm / EU < 210mm x 180mm x 125mm
  Power Consumption	<10 W(TBC) for 3 OH and EU @28V

• 
  GNSS receiver for geostationary satellites

  • World-class navigation code and message generator for Korean satellite navigation systems
  • The code/message generator for navigation satellites generates navigation messages and codes to provide ultra-precise PNT services based on navigation data and correction data received from the ground
  • This task was designed to be applied to the KPS project and was developed to be suitable for Korean navigation satellites in consideration of system linkage

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  정지궤도 위성용 GNSS 수신기: Items, Specification에 대한 표 입니다.

  Items	Specification
  RF Characteristics	GPS L1 / L2C, Galileo E1
  Accuracy	Position : ≤ 30m(3D RMS), Velocity : 10cm/s
  Raw Data Accuracy	Pseudo-Range : 1m(RMS) / Carrier-Phase : 10mm(RMS)
  1PPS Accuracy	2us(RMS) / Sync to GPS Time Data
  Data Output Rate	1Hz
  TTFF	Cold Star ≤ 45min, Warm Start ≤ 20min
  Data Interface	MIL – STD – 1553B
  Radiation(TID)	> 100krad

• 
  Practical-Class Optical Gyroscope

  • Mounted within the satellite bus, this gyroscope detects rotation via light interference in fiber optics, supporting satellite stabilization and precise attitude control

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  실용위성급 광학형 자이로: Items, Specification에 대한 표 입니다.

  Items	Specification
  Range	< ± 20⁰ / sec(Full Performance), < ± 140⁰ /sec(Survival)
  BIAS Stability(1-hr)	< 0.01⁰/ hr(3𝛔)
  ANGLE Random Walk	< 0.001⁰/ √hr(1𝛔)
  Scale Factor Stability (12-hr)	< 200 ppm(3𝛔)
  Life	> 15 year(GEO)

• 
  ASIC-Based Multicore Controller for Satellite Onboard Computers

  • Development of a qualification model (QM) for a space-grade ASIC-based multicore controller to be used in onboard satellite computers
  • Establish a reliability evaluation system based on MIL-PFR-38535 or ESCC 9000
  • Develop high reliability ceramic package and assembly/manufacturing process

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  위성 탑재컴퓨터를 위한 ASIC기반 멀티코어 컨트롤러: Items, Specification에 대한 표 입니다.

  Items	Specification
  CPU Core	RISC-V 32bit Dual core processor
  Performance	200 MIPS / EDAC / Hardware Memory Scrubber
  Memory Controller	SRAM, PROM, SDRAM
  Peripherals	CAN, UART, 12C / SPI, PCI, GPIO, Ethernet
  Radiation	TID : 300 krad(TBD), SEL : 118 MeVcm2/mg(TBD)