Products > Ready-to-Fly Platforms > KRATOS 1U Cubesat Platform
HIGHLIGHTS
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All included, Ready to fly, just add your payload
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Custom configurable to fit tight budgets
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Room for 6 standard payload boards and 3 cameras
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USB 2.0 and I2C bus as standard
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LASER communications at 10Mbps available as an option
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Embedded antennas, magnetorquers, temperature and sun sensors
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Includes ICEPS all-in-one OBC, EPS, SDR radio and ADCS systems
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Battery has temperature sensors, passive heater and optional active heaters
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Automated release and deploy of panels, antennas and room to control 2 more devices
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Designed for LEO missions and requirements
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Manufactured according to NASA and ESA space standards and materials
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Functional, performance, thermal bake out and vibration tests provided with documentation.
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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.
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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
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Includes:
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Full Engineering Support
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Test Reports
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EUDP, ICD
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UN38.3, CoO, MSDS
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Shipped in Pelican 1300 Case
PERFORMANCE
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EPS:
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100W max effective delivered power
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Payload power available from 20W (min) to 95W (max)
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4 Power Rails: 5V@25W, 3V3@10W, 12V@50W and 1 unregulated power rail
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1 APU connection available
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UMPPT 4-channel, 2A each, Solar power manager
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Fast 2A dual Li-poly charger onboard
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Solar array power from 3.75 W minimum to 16 W maximum
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Solar Cell Efficiency: 28% (High power) or 19% (low cost)
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Battery:
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BA03/S slim high energy density array
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25Whr minimum, 100Whr maximum
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Embedded temperature sensor
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Standard graphene passive heater
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Optional active heater
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ADCS:
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6 sun sensors input from all walls
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Integrated IMU
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Optional Novatel GPS w/antenna
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Detumbling and B dot libraries included
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Embedded Magnetorquers MT02:
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Nominal Magnetic moment: >0.14 Am2
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Saturation Magnetic moment: >0.48 Am2
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Linearity: +/- 4% across operating design range
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Residual moment: <0.0075 Am2
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Torque: 3.66 µNm @ 3.2 mTesla (1U mass)
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Angular acceleration: 1.75 Rad/sec-2 (1U mass)
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B-center = 3.0 Gauss
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B-corners = 3.1 Gauss
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Typical resistance: 14.1 to 14.7 ohms @ 25°C
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Random Vibration: 16g rms
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Z Magnetorquer MT01:
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Nominal Magnetic moment: >0.19 Am2
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Saturation Magnetic moment: >0.85 Am2
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Linearity: +/- 4% across operating design range
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Residual moment: <0.0045 Am2
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Torque: 5.36 µNm @ 7.2-3 Tesla (1U mass)
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Angular acceleration: 3.2-3 Rad/sec-2 (1U mass)
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B-center = 8.9 Gauss
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B-corners = 14.5 Gauss
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Typical resistance: 4.1 to 4.7 ohms @ 25°C
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Random Vibration: 16g rms
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Sun Sensor(6):
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Analog, GPIO, 5 to 16V digitized by ADCS
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Linear response range from 0.2V to 5V
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Working current: 50 mA
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Working FOV: 65 degrees H/V
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Temperature sensor(6):​
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Analog, GPIO, 4 to 12V​
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4 of them digitized by the OBC
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Linear response range from 0.3V to 1.5V
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Working current: 80 mA
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Working temperature: -65 to 135C
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SDR Radio:
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Epiq Z2 ARM9 SDR
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SDR radio from 70MHz to 6GHz
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One Transceiver port and 2 Receive only ports
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Embedded Antennas:
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Band Range: VHF to L-band
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Gain:
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Monopole configuration = 2.1 dB max
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Dipole configuration = 3.1 dB max
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Extended Monopole = 2.3 dB max
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Lambda: from 1/4 to full wave
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Optional active S-band patch with 6 dBi gain, 120 degrees aperture
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Optional active L-band patch with 6 dBi gain, 105 degrees aperture
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OBC:
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Xilinx ARM9 dual core @733Mhz OBC
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Preinstalled Linux IIOS with full libraries
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32GB to 512GB SSD radhard storage
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24 onboard sensors, room for 32 GPIO inputs
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USB and i2C concurrent buses with room for 8 user devices or payloads
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512 MB of DDR3L RAM
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32 MB of QSPI flash storage for uboot bootloader Linux kernel, and root file system
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480 Mbps bus speed (USB 2.0)
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Shielding:
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SEAM/NEMEA A-class
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Regulates temperature to a comfortable and steady 10C inside the spacecraft
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Stable and steady temperature trough the complete thermal cycle
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Deters and attenuates Alpha and beta particles, Gamma and X-rays and L-neutrons
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Can withstand 140C on the outside while providing 20C inside the spacecraft
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PROPERTIES
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Mass (exact mass depends on configuration):
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1 panel : 460 g minimum
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2 panels: 500 g minimum
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3 panels: 540 g minimum
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Al T6061 structure w/ 2 tunable pushers and 1 activation switch
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Solar panels thickness:
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Folded:
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1 panel: 2 mm
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2 panels: 4 mm
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3 panels: 6.25 mm
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Unfolded: 1.5 mm
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Operating Temperature: -80 to +140°C
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Radiation Tolerance: 4 years minimum in LEO
COMPOSITION
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Only TML and CVCM < 1% materials used, NASA and ESA approved:
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Contact sensors: Gold Deploy and Release
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Actuators:
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Deploy: Spring operated
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Release: EXA artificial muscles MDR/R1C, 50 grams max torque
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Cell Material: GaAs (High power) or mono crystalline Silicon (low cost)
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Cell Interconnector: Invar Silver plated
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PTFE (Teflon) space grade cables, multi-strand, silver plated copper (AWG26, AWG24)
TESTS
All platforms are provided with reports regarding the following tests:​
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Thermal Bake out (10E-5 mbar @ 50C for 72 hours)
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Full vibration test for Falcon 9, Electron, Soyuz, Dnepr and Long March 2D
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QT and AT is performed on the unit to be shipped
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