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Products > Ready-to-Fly Platforms > KRATOS 1U Cubesat Platform




  • 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

  • Battery has temperature sensors, 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

KRATOS 1U Cubesat Platform:

1-Step solution, just add your payload

From € 44,000

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.

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 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. 

Availability:  8 to 16 weeks


  • Full Engineering Support

  • Test Reports


  • UN38.3, CoO, MSDS

  • Shipped in Pelican 1300 Case


  • 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 reports regarding the following tests:​

  • Thermal Bake out (10E-5 mbar @ 50C for 72 hours)

  • Full vibration test for Falcon 9, Electron, Soyuz, Dnepr and Long March 2D

  • QT and AT is performed on the unit to be shipped



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Solar Array w/embedded antennas and magnetorquers



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