Aerospace Technology

Space Products and Services


  Electric Propulsion for Small Satellite Propulsion System



 Satellite uses propulsion system for attitude control and orbit control but there is not much selection of propulsion system (mainly cold gas propulsion system) for small satellite application.
 Most of the propellants used for satellite propulsion system are hazardous and toxic so they are not suitable for small satellite developed in Universities or Research Centers due to safety issues. ATI's microwave engine is one type of electric propulsion system which uses Xenon gas as propellant. This propellant is inert gas so there is no problem on the safety.


ATI develops other propulsion system such as Pulsed Plasma Thruster (PPT), Hall Effect (SPT) Thruster (5mN, 10mN, 15mN, 30mN, 80mN), and others. Also, ATI provides Standard Heater type Hollow Cathode (operates with Xenon purity of 99.999%) and Xenon gas for electric thrusters.

Please contact us for details.


  Nano-Satellite


  In the early stages of space development, there were a simple mission for on-orbit testing of new satellite bus components such as the ones which ATI has developed or student experiment but as present, there are no such opportunities.              
 In order to advance the new technology, development, designing, and ground testing of space products is important but actual space flight is most important to confirm the new technology so there are lot of needs for the small space laboratory.

 There will be a lot of needs for simple, low-cost, small satellites which can meet the needs of this kind of on-orbit testing of newly developed space equipments.         
 ATI is developing small satellites (1 kg to 100 kg) to realize the above experimental needs and to advance the nano technology for future small, nano-satellites. From this development, ATI has developed microwave engine system and reaction wheel to meet this goal.

Also, ATI provide a standard 3U and 6U CubeSat Bus System.
For details, please contact us.



  Small to Large Satellite


  In cooperation with foreign satellite manufacturer and R&D center, ATI provides various type of flight proven satellite systems to meet each customers needs from small to medium LEO satellites to medium to large commercial GEO satellites. With the use of flight proven standard satellite bus, ATI can provide fast delivery with low cost.
ATI can also propose a complete system with our launch service.
Please contact us for details.



  Momentum/Reaction Wheel for Satellite Attitude Control


















          MAI-400





























Single Axis Momentum/Reaction Wheel





 
            CMG




  For attitude control of satellite, delicate spinning top (wheel) is used.
 
This is usually called "Momentum and/or Reaction Wheel" and it is very expensive and has been only developed for medium to large satellite.                      
 Present advanced small satellite will require reaction wheels for its attitude control so ATI is developing this reaction wheel for small satellite application. We also distribute 3 axis reaction wheel in one package and single axis momentum / reaction wheels for small to medium satellite.     
 Control electronics is built into this wheel so interface is very simple. These momentum and reaction wheels had been used in many satellite engineering, ground test, and flight models.

3 Axis Reaction Wheel For Nano and Micro Satellite

MAI-400: Complete 3 Axis ADACS. It consists of 3 RW, 3 magnetic torquers,
      3 axis magnetometer, and 2 Earth Horizon Sensor (SES) or               Star Tracker (SS) as well as fully programmed ADACS computer.
      Momentum Storage 9.35 mNms Max Torque 0.635 mNm (each axis)
      Power 3.2W (Peak Slew)  Voltage 5 Vdc Pointing Accuracy 0.1 deg
      (using SS), 1 deg (using SES)  Size 100x100x52mm                  Magnetic torquer 0.15 Am2

MAI-400A: 1 Axis Reaction Wheel (RW) with Wheel Driver.
      Momentum Storage 9.35 mNms  Max Torque 0.635 mNm
      Maximum speed 10,000 rpm   Power 0.85W (Steady State@500rpm)
      Voltage 5 Vdc  Size 33x33x38.4mm

MAI-400B: ADACS Computer and Magnetic Torquers. It consists of 3 magnetic
      torquers, and 3 axis magnetometer as well as fully programmed
      ADACS computer.

MAI-400C: Complete 3 Axis ADACS. It consists of 3 RW, 3 magnetic torquers,
      and 3 axis magnetometer as well as fully programmed
      ADACS computer.

SES: Static Earth Sensor (SES) Camera (Use with MAI400)
      Power 40mA/sensor  Voltage 3.3 Vdc  FOV: 60 deg (coarse),           >7 deg (fine)   Resolution: >1 deg (coarse), <0.25 deg (fine)
      Size 43.3x32x32mm  Mass: 33g   CMOS camera

SS: Star Tracker (SS) (Use with MAI400)
      Power 1.5W (average)  Voltage 3.3 Vdc                         Accuracy: 0.013 deg (cross boresight)  Acquisition Time 0.13 sec          (acquisition), 0.105 sec (Track, typical) Max Tracking Rate: >1 deg/sec
      Star Catalog 6.0VM   Size 42.3x47.1x49.5mm  Mass: 193.4g

Also, provides Dynamic Simulator (Standalone and Hardware In The Loop (HITL)) test set for MAI400 which verifies and validates all software and hardware functions in the bench top setting. It can be tailored for the dynamics of any arbitrary spacecraft. Please inquiry for details.


We also have
single axis momentum/reaction wheels ranging from 12 to 100 Nms (Momentum Storage) and 75 to 130 mNm (Torque). Please contact us for the details. Following are few specifications of our wheels:

Angular Momentum (Nms) 12 25 50 100
Max Torque (mNm) 100 75 75 130
Max. Power (W) 9 12 12 35
Nominal Power (W) - - - -
Mass (kg) 7.3 6.0 7.9 13.6
Voltage (V) 24~34 24~34 24~34 24~34
Size (mm) 260x128 343x120 343x120 420x134
Lifetime (years) ≧8 ≧15 ≧15 ≧15
Operating Speed (RPM) 2,500 5,100 5,100 6,000
Operating Temperature (℃)  -5 - +45 -5 - +50  -5 - +50  -5 - +45 
Space Heritage Yes Yes Yes Yes


We also have
Control Momentum Gyro (CMG) with following specifications:

Angular Momentum (Nms) 5 25 1500
Max Torque (Nm) 6 25 200
Gimbal Rate Resolution (deg/s) 0.01 - ≦0.001
Gimbal Rate Range (deg/s) 0.01 - 72 - -
Gimbal Angle Resolution (arcsec) - - ≦1
Gimbal Angle Accuracy (arcsec) - ≦5minutes ≦5 (3σ)
Gimbal Rotation Range (deg) - 360 ±180
Max Power Consumption (W) 35 55 133
Mass (kg) ≦10 ≦18 ≦135
Dimension (mm) - Φ273x373 980x700x700
Lifetime (years) ≧5 ≧8 ≧10
Operating Temperature (deg C) - -5 - +45 -10 - +45





  Sun Sensor



     NanoSSOC-D60 Sun Sensor






     NanoSSOC-A60 Sun Sensor
 ATI provides flight proven, two axes, high performance, and low cost MEMS based sun sensors for small satellite application from Solar MEMS Technologies.

Major Parameters of Digital Interface Sun Sensor, nanoSSOC-D60

Type: 2 orthogonal axes
Field of View (FOV): ±60 deg
Accuracy: < 0.5 deg
Precision: < 0.1 deg
Power Supply: 3.3 V / 5 V
Power Consumption: < 23 mA
Size: 43 x 14 x 5.9 mm
Mass: 6.5 gr
Communication: UART, I2C or SPI
Connector: 10 pin micro-connector
Temperature range: -30 to +85 deg C

Major Parameters of Analog Interface Sun Sensor, nanoSSOC-A60

Type: 2 orthogonal axes
Field of View (FOV): ±60 deg
Accuracy: < 0.5 deg
Precision: < 0.1 deg
Power Supply: 3.3 V / 5 V
Power Consumption: < 2 mA
Size: 27.4 x 14 x 5.9 mm
Mass: 4 gr
Interface: 4 V outputs
Connector: 10 pin micro-connector
Temperature range: -30 to +85 deg C


Please contact us for details.


  Star Tracker




          μSTARTM


        Star Tracker ST
 ATI provides low cost, flight proven high performance Star Tracker for LEO and GEO satellites.

Major Parameters of Star Tracker, μSTARTM

  μSTAR-100L  μSTAR-100M  μSTAR-200M  μSTAR-200H  μSTAR-400M 
 FPA  Sony CCD HAS2 HAS2/STELLAR  STELLAR  STELLAR 
Accuracy (1σ)
Cross-boresight 
 20 arcsec 5-20 arcsec  1-20 arcsec  <1 arcsec  1-5 arcsec 
Average Power   <5W <5W  8-10W <10W  <18W 
Update Rate  1 Hz  1 Hz  10 Hz  10 Hz  100 Hz 
FOV  24 deg  28 deg  28 deg  8 deg  10 deg 
Earth/Sun
Exclusion Angle 
35 deg  35 deg  35 deg  25 deg  25 deg 
DPE Mass (kg)   0.9 0.9  1.2  1.2  1.2 
CHU Mass (kg)  0.35  0.9  0.9  2.0  2.5 
Total Mass (kg)  1.25  1.8  2.1  3.2  3.7 
Note: DPE: Digital Processing Electronics; CHU: Camera Head Unit

Total Ionizing Dose (TID) > 100 and 300 krad (Si) (option)
Single Event Latchup (SEL) > 80 MeV/mg/cm2
Single Event Upset (SEU) < 10-3 errors/system-day
Neutrons > 2x1012 n/cm2


Major Parameters of Star Tracker, ST-APS-1

Instrument Mass (including 30 deg baffle): 4.2 kg
Power consumption: 10.6 W (Cooler ON))
Input Voltage: 28 to 48 Vdc
FOV: 20 deg x 20 deg
Accuracy: 3.0 arcsec (Pitch/Roll, 3 sigma)
       36 arcsec (Yaw, 3 sigma)
Update Rate: 2/4/5/8 Hz
On-orbit Lifetime: 8 years (LEO)/15 years (GEO)
Interface: RS-422
Acquisition Time: 2.4 seconds (typical)
Slew Rate: <0.3 deg/sec (full performance)
       0.3 to 3.0 deg/sec (reduced performance)
Operating temperature: -40 to +50 deg. C


Major Parameters of Star Tracker, ST-APS4-1


Instrument Mass (including 26 deg baffle): 2.3 kg
Power consumption: <10 W (Cooler ON), <6 W (Cooler OFF)
Input Voltage: 20 to 35 Vdc
FOV: 20 deg
Accuracy (EOL Rms): <6.0 arcsec (Pitch/Roll, 3 sigma)
               <24 arcsec (Yaw, 3 sigma)
Update Rate: 10 Hz (Max)
On-orbit Lifetime: 15 years (GEO)
Interface: RS-422/MIL-STD-1553B
Acquisition Time: <0.1 seconds
Slew Rate: <0.3 deg/sec (full performance)
       0.3 to 3.0 deg/sec (reduced performance)
Operating temperature: -30 to +55 deg. C
Dimension: 130x130x259 mm (including baffle)


ATI also have other Star Tracker to fit your needs so please contact us for details.

ATI can jointly develop a new Star Tracker which fit your needs with the use of our Rad Hard commercial electronic board technology. Please contact us for your interest.


  Gyro





 ATI provides flight proven high performance Inertial Gyros for LEO and GEO satellites.

Major Parameters of Inertial Gyro, IAS-1-4-C

Configuration: 4 gyroscopes (3 orthogonal and 1 skewed gyros)
Measurement Range: -2≦ω≦2 deg/s
Pulse Factor: 1x10-4 deg/pulse
Bandwidth: ≧5 Hz
Constant drift: ≦5 deg/hr
Random drift: ≦0.3 deg/hr
Supply Voltage: ±12, +28 V
Power Consumption: ≦8.7W (+12V), ≦8.0W (-12V), ≦22W (+28V)
Mass: 3.5 kg (Gyro), 4.2 kg (Electronics)

Major Parameters of Inertial Gyro, IAS-1-4-A

Configuration: 4 gyroscopes (3 orthogonal and 1 skewed gyros)
Measurement Range: -2.5≦ω≦2.5 deg/s
Pulse Factor: 1x10-4 deg/pulse, 1x10-2 deg/pulse
Bandwidth: ≧10 Hz
Constant drift: ≦5 deg/hr
Random drift: ≦0.3 deg/hr
Supply Voltage: 30 to 42V
Power Consumption: 35 W
Mass: 3.1 kg (Gyro), 7.1 kg (Electronics)


Please contact us for details.


  GaAs Solar Cell, Solar Panel, and Solar Array



  30.6x40.3mm Solar Cell Assembly


 40x80mm Solar Cell Assembly Type 1


 40x80mm Solar Cell Assembly Type 2

 ATI provides low cost, flight proven Crystalline Silicon solar cell (average efficiency of 15%), low cost, flight proven high efficiency Triple Junction GaAs solar cell, Solar Panel, and Solar Array Systems for LEO and GEO satellite.

Major Parameters of Triple Junction GaAs Solar Cell

Average Efficiency (BOL): 28 to 30%
Mass: 84mg/cm2
Available Size: 40mmX60.5mm (Standard), 30.6mmX40.3mm (Standard), 20mmX40mm, 20mmX20mm, 39.5mmX68.9mm (Standard), 40mmX80mm (Standard), 80mmX80mm (No Coverglass), 60mmX120mm (No Coverglass)
Can provide both bare cell and CICs.
Annual production capacity: >30KW

Major Parameters of Silicon Solar Cell

Average Efficiency (BOL): approx. 15%
Available Size: 20mmX40mm
Can provide both bare cell and CICs.

ATI can also provide Al honeycomb and CFRP/Al honeycomb Solar Array Substrate panel, cell integration (pasting, wiring, etc.) to substrate panel, and performing various testing for space application. Also, ATI can provide PCB solar panel with solar cells which can be used for CubeSat. Please contact us with your requirements including cell size.

ATI can also provide a complete Solar Array System including cell, panel, hinge, york, solar array drive mechanism (SADM), deployment mechanism for Silicon based cell and GaAs based cell.

ATI also supplies Crystalline Silicon solar cell (average efficiency of approx. 18%), Triple Junction GaAs solar cell (average efficiency of approx. 32 to 35%) for flat panel use, and Triple Junction CPV GaAs solar cell (average efficiency of approx. 40%@ 500 sun concentration ratio) and receiver for ground solar power system. Please contact us for details.


  Battery



    Nickel Hydrogen Battery

      
      Nickel Cadmium Battery

    
        Lithium Ion Battery

      
          Zn-Ag Battery

      
          Thermal Battery
 ATI provides primary and secondary batteries for satellite and launch vehicle.

Secondary Batteries for On-Board Satellite

  • Lithium Ion Battery: 2.5 Ah~120 Ah
  • Nickel Cadmium Battery: 6 Ah~70Ah
  • Nickel Hydrogen Battery: 40 Ah, 70 Ah

Primary Batteries for Launch Vehicle

  • Zn-Ag Battery: 1 Ah~70 Ah
  • Thermal Battery: 19.8 As~10,000 As

Please contact us for details with your requirements.


  Thermal Control (Optical Solar Reflector (OSR), Multi-Layer Insulation (MLI), Heat Pipe, Thermal Coatings)



            OSR


           Heat Pipe
 ATI provides low cost, flight proven satellite thermal control components (Optical Solar Reflector (OSR), Multi-Layer Insulation (MLI), Heat Pipe and Heat Pipe Embedded Honeycomb Panel).

Major Parameters of OSR

Absorptivity (αs): ≦0.08~0.1
Emissivity (εh): ≧0.76~0.8
Thickness: 0.1mm
Available size: 40mmX20mm, 40mmX40mm
Annual production capacity: 100,000 pieces

Multi-Layer Insulation (MLI)

Provide various types of MLI ranging from low to high temperatures. Manufacturing can be provided by either providing your requirements or providing a CAD drawings. Also, provides kapton tape and aluminized kapton tape.

Heat Pipe

Provide various type (single, dual, flexible, cryogenic, high temperature, variable conductance) heat pipes and deployable radiator for your specific requirements. Also, provide heat pipe embedded honeycomb panel. Please contact us with your requirements.

Thermal Coatings (Organic and Inorganic)

Provide various types of space use thermal coatings (white, black optical, transparent, electrically conductive, etc.) for your specific requirements. Please contact us with your requirements.

Please contact us for details.


  Satellite Propulsion System and Components



    Propellant Tank           Thruster

      
    Composite/Metallic Propellant Tank


            Valve Driver

    
             Nozzle
 ATI provides design and development of satellite propulsion systems and components such as thruster, propellant tank, pressurant tank, filters, etc.

1. Major Propulsion Systems
  • Monopropellant Hydrazine and ADN Propulsion System Design, Development, Integration
  • Bipropellant Propulsion System (MMH/MON, etc) Design, Development, Integration
  • Solid Propellant Propulsion System Design, Development, Integration
  • Electric Propulsion System Design, Development, Integration
  • CubeSat Propulsion System Design, Development, Integration
  • Propellant Feed System Design, Development, Integration
2. Propulsion Components
  • Thruster (Monopropellant Hydrazine thruster (0.2N, 1N, 5N, 20N), Bipropellant (MMH/MON) thruster (10N, etc.), green propellant ADN thruster (1N), Bipropellant (Hydrogen Peroxide/Ethanol) thruster (430N), etc.)
  • CubeSat Propulsion system and thruster (H2O2, etc)
  • Propellant Tank (Bladder, Diaphragm, and Surface Tension Expulsion Device (PMD); Metallic or Composite/Metallic; hydrazine, MMH, MON, ADN, etc. propellants) Development
  • Pressurant Tank (Titanium alloy or Composite; Operating pressure of 15-30 MPa; Volume of 2-50 liter) Development
  • Propellant filter
  • Propellant valves and Latch valve
  • Propellants (hydrazine, MMH, MON, green propellant ADN, etc.)
  • Rocket nozzle and rocket dome manufacturing
Please contact us for details.
ATI also develops space qualified valve drivers (including miniature size valve drivers) so please contact us for details.


  Space Radiation Hardened Electronics (i.e., Computers)











        PROTON-200k





















         PROTON-300k











         PROTON-400k














         Proton200k-L


















 
           CSP











           IPC5000/7000











































           ECC-1
 ATI provides flight proven, low cost, rad hard, high performance electronics (including computer boards, etc.) for LEO and GEO satellites. Uses Space Micro's patented Time Triple Modular Redundancy (TTMRTM) and Hardened Core (H-CoreTM) technology to migitage, detect, and correct radiation effects in space environments.

Major parameters of PROTON-200kTM DSP Processor Boards

Processor:
Fixed Point Version: TI 320C6XXX, 1GHz, 8,000 MIPS native
  • 4,000 MIPS at 1E-4 unrecoverable errors/day
  • L1 32KB (16/16KB) Program/data Cache
  • L2 1MB (Cache/Mapped RAM, flexible allocation)
  • 3 Timers, 32-bit
Floating Point Version: TI 320C6XXX, 300MHz, 1,800 GFLOPS native
  • 900 MFLOPS/ 1,200 MIPS at 1E-4 unrecoverable errors/day
  • L1 8 KB (4/4KB) Program/Data Cache
  • L2 256KB (64KB Cache/Mapped +192KB Mapped RAM)
  • 2 Timers: 32-bit
Power: 5-10 Watts (standard board), full speed
Memory: 128 MB to 32 MB SDRAM w/EDAC & 256 or 64 MB without EDAC
      1 MB EEPROM to 8 Mbyte (option),
      512 MB RH Flash (option)
Radiation Tolerance:  SEL > 63 LET (MeV-cm2/mg)
               SEU < 1 per 1,000 days (1.0 E-4, 90% W.C. GEO, Orbit
                    dependent)
               TID > 100krad (Si), Orbit dependent
               SEFI 100% recoverable
Operating Temperature: -24˚C to +61˚C
Interface: 32bit, 33MHz I/O bus
OS: TI Code Composer Studio

Major Parameters of PROTON-300kTM FPGA Reconfigurable Computer

FPGA: Xilinx XC5VX155T using either
  • Xilinx Platform Flash Memory (Engineering Model)
  • Rad Hard TMR Flash (Flight Model)
2 Channels LVDS Video
SGMII Gigabit Ethernet, 10/100/1000 BaseT Interface
SDLC IMU via RS422 Interface
Four 4M X 18 QDR2 + SRAM 200MHz (currently operating at 180MHz)
32 bit, 33/66MHz PCI-104 Interface (currently operating at 33MHz)
Memory: 8GB radiation hardened flash memory
Operating Temperature: -24˚C to 61˚C
Power: ≈ 5-7 W for DSP, FPGA is dependent on configuration
Radiation Tolerance: TID: > 100krad (Si)
              SEFI: 100% recoverable
              SEU: < 1.0E-4 unrecoverable errors per day
              SEL: Immunity at >63 LET (MeV-cm2/mg)

Major Parameters of PROTON-400kTM Single Board Computer
  • Freescale 2020 high performance processor
  • 1 GHz, 32-bit (per core) dual core processor with 36-bit physical addressing
  • Integer
  • < 1 per 1,000 days (1E-4 errors/day SEU rate, 90% W.C. GEO, Orbit dependent)
  • >100 krad (Si) total dose tolerance
  • Single Event Latchup (SEL) Immunity >63 LET (MeV/mg/cm2)
  • 32 KByte instruction & data cache/core
  • 512 KByte L2 cache
  • 128 to 512 MB DDR 3/2 with EDAC
  • 1 MB EEPROM
  • 32 Gb radiation hardened flash
  • Power: 8 - 12 watts (depending upon peripherals, speed)
  • Compact PCI 3U/6U/PCI-104S or custom
  • Interfaces: 32 bit, 33MHz I/O bus
  • OS: Linux Board Support Package (BSP) or VxWorks BSP
  • Operating Temperature: -24˚C to 61˚C

Major parameters of PROTON-200k-LTM Lite DSP Processor Boards for CubeSat

Processor:
Fixed Point Version: TI 320C6XXX, 1GHz, 8,000 MIPS native
  • 4,000 MIPS at 1E-4 unrecoverable errors/day
  • L1 32KB (16/16KB) Program/data Cache
  • L2 1MB (Cache/Mapped RAM, flexible allocation)
  • 3 Timers, 32-bit
Floating Point Version: TI 320C6XXX, 300MHz, 1,800 GFLOPS native
  • 900 MFLOPS/ 1,200 MIPS at 1E-4 unrecoverable errors/day
  • L1 8 KB (4/4KB) Program/Data Cache
  • L2 256KB (64KB Cache/Mapped +192KB Mapped RAM)
  • 2 Timers: 32-bit
Power: 1.5 Watts
Memory: 512 MB SDRAM w/EDAC
      1 MB EEPROM to 8 Mbyte (option),
      8 Gb RH Flash (option)
Radiation Tolerance:  SEL > 63 LET (MeV-cm2/mg)
               SEU < 1 per 1,000 days (1.0 E-4, 90% W.C. GEO, Orbit
                    dependent)
               TID > 100krad (Si), Orbit dependent
               SEFI 100% recoverable
Interface: 32bit, 33MHz I/O bus
OS: TI Code Composer Studio (option)
   TI DSP/BIOS RTOS (option)
   JTAG debugging support

Major parameters of CubeSat Processor (CSP) Board

Processor: Xilinx Zynq-7020
  • 2.5 DMIPS/MHz per CPU
  • CPU frequency: ≦1 GHz
I/O: 26 x MIO (Multiplexed IO), 60 x HR Select IO (High Range Select IO)
** Not all interfaces can be used simultaneously
Power: <2.9 Watts
Memory: 32 GB NAND Flash
      4 GB DDR3 SDRAM (2 GB when EDAC is active)
Size: 1U (90x89mm)
Radiation Tolerance:  SEL: No Destructive Events
               SEU: Unmitigated - Same SEU rates as a commercial                      Xilinx 7 family Zynq part
               TID: 30krad (Si)
               SEFI: Mitigated with watchdog for ARM Cores
OS: Wumbo GNU/Linux
Operating temperature: -20 deg C to +70 deg C

Major Parameters of IPC5000/7000TM Image Processing Computer

The IPC5000/7000TM image processing platform is a three board set (Single Board Computer (SBC), Solid State Buffer, Image Processing Computer(IPC)) that combines high performance, low power radiation hardened computing and high-speed mass memory to meet the challenges of the space imaging environments.

SBC:
  • Floating point DSP - 900 MFLOPS at 1E-4 unrecoverable errors/day
  • 128 MB EDAC protected RAM
  • 4 Gb rad hard flash memory
  • Programmable speed UARTs
  • 1 Mbps synchronous serial ports
  • Variable power control
Solid State Buffer:
  • 64 Gbit high-speed SDRAM
  • 2 Gbps input data rate
  • Optional EDAC
IPC:
  • Dual input fibre optic input >1 Gbps
  • Virtex 5 or 7 FPGA processing with Reconfigurable bitmaps
  • Local RAM buffering
  • 128 MB EDAC protected RAM
  • 4 Gb rad hard flash
  • Gigabit Ethernet download output
    • Fibre optically coupled IF
    • LVDS option available
  • Embedded, image processing
    • Real-time 12 bit JPEG compression
    • Real-time non-uniformity correction
    • Multiple image channels
    • Channel formatting and packetization
Radiation Tolerance:
  • >100 krad (Si) total dose tolerance
  • Single Event Latchup (SEL) Immune >70 MeV/mg/cm2
  • No SEFI
  • SEU tolerance 1E-4 unrecoverable errors/day
Power: 40 watts worst case configuration (depending upon peripherals, speed)


Major Parameters of ECC-1 2.5 Gbps Forward Error Correction (FEC) IC

Radiation hardened FEC IC is ideal for all space-based RF and laser communication links (Space to Space, Space to Aircraft, Space to Ground), regardless of LEO, MEO, or GEO. It uses proprietary concatenated Reed-Solomon/BCH code with 8 different encoding/decoding settings to provide extremely low bit error rate with excellent performance on fading and burst error channels.
  • Data Rate: 2.5 Gbps (for FEC code rate ≧0.937)
  • Bit Error Rate: 1.0E-10 at 6dB
  • FEC Code: RS (outer) / BCH (inner) concatenated with 8 encoding/decoding settings
  • Total Ionizing Dose (TID): >100 kRad (Si)
  • Single Event Latchup (SEL): Immune to >80 MeV-cm2/mg)
  • Single Event Upset (SEU): 1.0E-4 upsets/device-day (GEO)
  • Operating Temperature: 0 to 70 C
  • Storage Temperature: -40 to +150 C


Other boards are also available such as Standard SpaceWire boards, Space Qualified GPS Receiver Board, ProtonX-BoxTM Avionics Suite, Proton2X-BoxTM Avionics Suite, Rad Hard Internet Protocol Encryptor, etc.
Please contact us for details of the above boards.


  Satellite Communication Equipments



      X-Band QPSK Modulator


  X-Band Linearized Power Amplifier





    μSTDN S-Band Transponder













     μXt X-Band Transmitter


   μKaTx Ka-Band Transmitter
 X-Band QPSK Modulator is used in data transmission system on-board earth observation and scientific satellites. This modulator consists of local oscillator, QPSK modulator, microwave filter, microwave amplifier, and data encorder by using integrated design technique to reduce mass and size.

Major Parameters of X-Band QPSK Modulator:
  • Career Frequency: 7.9~9 GHz
  • Data Rate: up to 300 Mbps
  • Output Power: 0~6 dBm
  • Phase Imbalance: <±4°
  • Amplitude Imbalance: <1 dB
  • DC Power Consumption: <10.5 W
  • Data Interface: LVDS, ECL

Other Communication Equipments:

Major Parameters of X-Band Linearized Power Amplifier:
  • Bandwidth: 7250 – 7750 MHz
  • Noise: <10dB
  • Input Power:  -15dBm per channel up to 10 channels
              -12dBm per channel up to 5 channels
  • Output Power: 0.25 W RF per channel up to 10 Channels @ -15dBm input each
              0.5 W RF per channel up to 5 Channels @ -12dBm input each
  • Gain: >=5W Single tone
  • Operating Temp: -15℃ to +55℃
  • Radiation Tolerance (TID): >30krad (Si) Over 1 year
  • Low cost compared to other competitors
Flown on NASA GSFC (Goddard Space Flight Center) IRIS (an Earth Observation satellite program for monitoring the Sun).

Major Parameters of μSTDNTM S-Band Transponder:

  • Transmit frequency: 2200-2300 MHz
  • Receive frequency: 2025-2120 MHz
  • RF Output: 5 to 8W
  • Data Rate: 5Mbps (transmit), 2-128kps (receive)
  • Modulaton: BPSK, PCM, PSK
  • Input Power: 28±6Vdc
  • Power Consumption: 35W (max., transmit), 6W (max, receive)
  • Radiation Hardened:
    • TID 100 krad
    • No SEL or SEFI (>120MeV/mg/cm2)
  • Mass: 2.5 kg
  • Size: 127x127x102 mm
  • CCSDS compliant
  • Low cost compared to other competitors
Flown on NASA GSFC (Goddard Space Flight Center) IRIS (an Earth Observation satellite program for monitoring the Sun) and NASA ARC (Ames Research Center) LADEE (Lunar Atmospheric Dust Environment Explorer). 

Major Parameters of μXTx-200TM X-Band Transmitter:
  • RF Output Frequency Range: 7.7 to 8.5 GHz
  • RF Output Power: 1W to 10W (Factory selectable, custom models to 25W)
  • Modulation: QPSK, OQPSK, 8APSK, 16APSK, 32QAM
  • Input Voltage: 18 to 40Vdc
  • Mass: <3 kg
  • Size: 208x153x66 mm
  • Radiation: Total Dose 100 kRad, Latch-up immune
  • Operating Temperature range: -24 to +65℃
  • Data Rate (Options): 100 kbps to 1 Gbps

Major Parameters of μKaTX-300TM Ka Band Transmitter:
  • RF Output Frequency Range: 20 to 32 GHz
  • RF Output Power: 3mW, 100mW, 2W, 5W
  • Power Dissipated: 28W, 31W, 45W, 68W
  • Modulation: 8-PSK, QPSK, OQPSK
  • Input Voltage: 18~40 Vdc
  • Mass: <3 kg
  • Size: 205x153x66 mm
  • Radiation Hardended: TID, SEU, SEL
  • Operating Temperature range: -30 to +65℃
  • Data Rate: 100 kbps to 3.2 Gbps

ATI also provides other space communication equipments such as Microwave Amplifiers (LNA, SSPA, TWTA), VHF to Ka Band Solid State Power Amplifier (SSPA), RF Amplifiers (LNA, SSPA) for SAR and Radiometers, Microwave Converter, Microwave Receiver, I/OMUX, DC/DC Converter, RF Power Amplifier for Acousto-Optic, etc.
For details including above products, please contact us.


  Satellite Antenna


 ATI provides various satellite communication antenna. Following are major antenna:
  • Dual Grid Antenna (C and Ku Band)
  • Single Offset Shaped Reflector Antenna (L, C, X, Ku, Ka Band)
  • Steering Spot Beam Antenna (Ku and Ka Band)
  • Gregorian Antenna (C, Ku, Ka Band)
  • Wide Beam Circular Polarization TT&C Antenna (L, S, C, X Band)
Please contact us for details.


  Space Environmental Monitoring Equipment


 ATI provides space proven on-board Space Environmental Monitoring Equipments, Space Weather Monitor and Space Radiation Dosimeter.

Space Weather Monitor can monitor Space Charging (internal and surface (optional)), Radiation Total Dose (TID), Single Event Effects (SEE). This unit is just 1 kg in mass and requires 2.5 W of power so it can be easily integrated to any satellite. This unit had been flown on various ESA and NASA satellites.

Space Radiation Dosimeter is a low power (approx. 1W), low mass (approx. 0.34 kg , high performance space dosimeter for measuring and monitoring single event and total dose radiation effects in space. It uses a UVEPROM sensor and radiation measurement sensitity, TID, is 1 Rad to 100 MRad (Si).

Please contact us for details.


  Spacecraft Design, Development, Engineering, and Application


 ATI provides design, development, and engineering support for launch vehicle and satellite (ranging from nano to large satellites and from scientific to commercial LEO, MEO, and GEO satellites) system, subsystems including structures, thermal control, propulsion systems (chemical (including green propellant) and electrical), electrical and power, attitude control, solar array, communication, antenna, etc., and related components. ATI's engineers have more than 25 plus years of experiences in designing and in research and development of various space programs in Japan and in international space communities.

 ATI also provides various support (including proposal writing and implementation) in realizing space application and space business. ATI feels that without space commercialization, there will be no future for space development so we put a lot of effort in this area.



  Classroom Satellite, EyasSATTM




 EyasSATTM: The Classroom Satellite
  • Enhance the learning experience of your satellite systems student
  • Teach systems engineering using hands-on hardware
  • Create satellite design curriculum using EyasSat for thorough understanding of systems and each subsystems
  • Demonstrate working satellite systems in your lab or classroom
EyasSat GEN5 is a set of circuit boards that plug together to form a complete lab satellite.
Each board or module functions as one of the subsystems. They stack by plugging them together using connect-through headers. We add the case with separation switch, solar panels, light sensors, and a thermal control surface to provide complete satellite simulator environment.

For EyasSat GEN5 Overview, please see this PDF.
Please click here for present users' list.

EyasSat is built to withstand the rigors of repeated classroom use, while still being delicate enough to teach students about proper handling procedures.
Engineers with hands-on experience with 15+ currently flying satellites have collaborated to construct the ultimate teaching tool for Satellite Engineering.

EyasSAT can be used for all kinds of students.

For less experienced students, EyasSat serves as a capable demonstrator, and working model.
For intermediate students, EyasSat's systems are an excellent way to provide hands-on experience to match classroom lecture on satellite design.
For advanced students, the provided interface documentation provides a solid foundation for the creation of custom "experiment" modules to add on to the EyasSat.

Please contact us for the price of EyasSat Basic Unit.

This price includes a User's Manual that contains a complete set of lab exercises and Owner's Manual with hardware details and lab setup information. We are pleased to also be able to include CD containing all the curriculum material from AFA Astro 331 course including lectures and instructor information. (exams and some copyrighted material are deleted) ATI also provides various support (including proposal writing and implementation) in realizing space application and space business. ATI feels that without space commercialization, there will be no future for space development so we put a lot of effort in this area.

For more details, please see EyasSat website

Please contact us for new modules and kits for EyasSat which are being in development or planned.


ATI has other products
Rad Hard CubeSat Boards, Deployment Mechanisms, Separation Bolt, Deployment Boom, Pointing Mechanism, Hinges, Actuator Motor, etc.) for satellite application so please contact us for these products.


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