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

ALL-TRL9
ITAR-Free-Product
NASA-SSIS-LISTED

HIGHLIGHTS

 

  • 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

​

Includes:  

  • Full Engineering Support

  • Test Reports

  • EUDP, ICD

  • UN38.3, CoO, MSDS

  • Shipped in Pelican 1300 Case

PERFORMANCE

  • 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

PROPERTIES

  • 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

COMPOSITION

  • 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)

TESTS

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

DOWNLOADS

PROVIDER:

EXA

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