EXA KRATOS 1U CubeSat Platform

EXA KRATOS 1U CubeSat Platform

€35000 - €125000

The EXA KRATOS 1U Spacecraft bus is a 1 step CubeSat solution that allows developers to focus on the payload and its mission: It includes everything needed for the spacecraft to work and even comes VTV tested, just integrate your payload and fly.

Includes:

  • Full Engineering Support
  • Test Reports
  • EUDP, ICD
  • 3, CoO, MSDS
  • Shipped in Pelican 1300 Case

Availability:  8 to 16 weeks

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  • Description
  • Features
  • Performance
  • Product properties
  • Materials
  • Testing
  • Documents

Description

The KRATOS SCB is completely configurable:  From a modest, standard CubeSat to a powerful SpaceTaxi in a 1U that can host up to 6 standard payload boards and 3 cameras delivering up to 100W of power, and LASER communications at 10Mbps. it has everything needed to fly: Onboard computer with pre-installed libraries, SDR Radio with an integrated power amplifier, a powerful EPS with 4 power rails, UMPPT Solar management couple to a fast battery charger, Deployable Multifunction Solar Arrays, automated deploy/release control to up to 4 devices, embedded monopole and dipole antennas from  VHF to L band, embedded magnetorquers, temperature and sun sensors in all walls, ADCS control with integrated Z axis magnetorquer, high power batteries, radiation-hardened SSD storage and even LASER communications at 10Mbps minimum.

​You can add or subtract features and expand capabilities accordingly to your project budget, the main idea is that you focus on your mission, we focus on the spacecraft.

  • All included, Ready to fly, just add your payload
  • Custom configurable to fit tight budgets
  • Room for 6 standard payload boards and 3 cameras
  • USB 2.0 and I2C bus as standard
  • LASER communications at 10Mbps available as an option
  • Embedded antennas, magnetorquers, temperature and sun sensors
  • Includes ICEPS all-in-one OBC, EPS, SDR radio and ADCS systems
  • The battery has temperature sensors, a passive heater and optional active heaters
  • Automated release and deploy of panels, antennas and room to control 2 more devices
  • Designed for LEO missions and requirements
  • Manufactured according to NASA and ESA space standards and materials
  • Functional, performance, thermal bake out and vibration tests provided with documentation.
  • Compatible and compliant with standard deployers and CubeSat Standard
  • EPS:
    • 100W max effective delivered power
    • Payload power available from 20W (min) to 95W (max)
    • 4 Power Rails: 5V@25W, 3V3@10W, 12V@50W and 1 unregulated power rail
    • 1 APU connection available
    • UMPPT 4-channel, 2A each, Solar power manager
    • Fast 2A dual Li-poly charger onboard
    • Solar array power from 3.75 W minimum to 16 W maximum
    • Solar Cell Efficiency: 28% (High power) or 19% (low cost)
    • Battery:
      • BA03/S slim high energy density array
      • 25Whr minimum, 100Whr maximum
      • Embedded temperature sensor
      • Standard graphene passive heater
      • Optional active heater
  • ADCS:
    • 6 sun sensors input from all walls
    • Integrated IMU
    • Optional Novatel GPS w/antenna
    • Detumbling and B dot libraries included
    • Embedded Magnetorquers MT02:
      • Nominal Magnetic moment: >0.14 Am2
      • Saturation Magnetic moment: >0.48 Am2
      • Linearity: +/- 4% across operating design range
      • Residual moment: <0.0075 Am2
      • Torque: 3.66 µNm @ 3.2 mTesla (1U mass)
      • Angular acceleration: 1.75 Rad/sec-2 (1U mass)
      • B-center = 3.0 Gauss
      • B-corners = 3.1 Gauss
      • Typical resistance: 14.1 to 14.7 ohms @ 25°C
      • Random Vibration: 16g rms
    • Z Magnetorquer MT01:
      • Nominal Magnetic moment: >0.19 Am2
      • Saturation Magnetic moment: >0.85 Am2
      • Linearity: +/- 4% across operating design range
      • Residual moment: <0.0045 Am2
      • Torque: 5.36 µNm @ 7.2-3 Tesla (1U mass)
      • Angular acceleration: 3.2-3 Rad/sec-2 (1U mass)
      • B-center = 8.9 Gauss
      • B-corners = 14.5 Gauss
      • Typical resistance: 4.1 to 4.7 ohms @ 25°C
      • Random Vibration: 16g rms
    • Sun Sensor (6):
      • Analog, GPIO, 5 to 16V digitized by ADCS
      • Linear response range from 0.2V to 5V
      • Working current: 50 mA
      • Working FOV: 65 degrees H/V
    • Temperature sensor (6):
      • Analog, GPIO, 4 to 12V
      • 4 of them digitized by the OBC
      • Linear response range from 0.3V to 1.5V
      • Working current: 80 mA
      • Working temperature: -65 to 135C
    • SDR Radio:
      • Epiq Z2 ARM9 SDR
      • SDR radio from 70MHz to 6GHz
      • One Transceiver port and 2 Receive only ports
      • Embedded Antennas:
        • Band Range: VHF to L-band
          • Gain:
            • Monopole configuration = 2.1 dB max
            • Dipole configuration = 3.1 dB max
            • Extended Monopole = 2.3 dB max
          • Lambda: from 1/4 to full-wave
      • Optional active S-band patch with 6 dBi gain, 120 degrees aperture
      • Optional active L-band patch with 6 dBi gain, 105 degrees aperture
  • OBC:
    • Xilinx ARM9 dual core @733Mhz OBC
    • Preinstalled Linux IIOS with full libraries
    • 32GB to 512GB SSD radhard storage
    • 24 onboard sensors, room for 32 GPIO inputs
    • USB and i2C concurrent buses with room for 8 user devices or payloads
    • 512 MB of DDR3L RAM
    • 32 MB of QSPI flash storage for uboot bootloader Linux kernel, and root file system
    • 480 Mbps bus speed (USB 2.0)
  • Shielding:
    • SEAM/NEMEA A-class
    • Regulates temperature to a comfortable and steady 10C inside the spacecraft
    • Stable and steady temperature trough the complete thermal cycle
    • Deters and attenuates Alpha and beta particles, Gamma and X-rays and L-neutrons
    • Can withstand 140C on the outside while providing 20C inside the spacecraft
  • Mass (exact mass depends on configuration):
    • 1 panel: 460 g minimum
    • 2 panels: 500 g minimum
    • 3 panels: 540 g minimum
  • Al T6061 structure w/ 2 tunable pushers and 1 activation switch
  • Solar panels thickness:
    • Folded:
      • 1 panel: 2 mm
      • 2 panels: 4 mm
      • 3 panels: 6.25 mm
    • Unfolded: 1.5 mm
  • Operating Temperature: -80 to +140°C
  • Radiation Tolerance: 4 years minimum in LEO
  • Only TML and CVCM < 1% materials used, NASA and ESA approved:
  • Contact sensors: Gold Deploy and Release
  • Actuators:
    • Deploy: Spring operated
    • Release: EXA artificial muscles MDR/R1C, 50 grams max torque
  • Cell Material: GaAs (High power) or mono crystalline Silicon (low cost)
  • Cell Interconnector: Invar Silver plated
  • PTFE (Teflon) space-grade cables, multi-strand, silver-plated copper (AWG26, AWG24)

All platforms are provided with tests reports regarding the following tests:

Test QT AT
Functional  ✔  ✔
Vibration  X  ✔
Thermal Cycling  X  ✔
Thermal Vacuum  X  ✔
Mechanical/Dimensional compliance  X  ✔
Continuity Isolation  ✔  ✔
Solar cells Cracks  ✔  ✔
Flasher Test  ✔  ✔
Sensors Test  X  ✔
OBC General interoperability Test  X  ✔
USB & I2C bus test  X  ✔
Deploy/Release Test  X  ✔
Antennas network VSWR Test  X  ✔
LASER emitter net power test  X  ✔
Batteries test  X  ✔
General Performance and day-in-the-life test  ✔  ✔