3U CubeSat Platform "PLT3"

CubeSat Platforms
CubeSat 3U Platform "PLT3"

3U Platform “PLT3”

NanoAvionics provides CubeSat platforms based on a modular and highly integral design which extends payload volume and saves development costs for customers.

Utilization of NanoAvionics’ platforms enables customers to concentrate on the most important mission goals dealing only with high level mission implementation problems such as payload integration and its support during the mission in orbit.

Example applications of the platform:

  • Educational missions
  • Technology in-orbit demonstration missions
  • Scientific missions
  • Commercial constellation missions and many others
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Platform Features

  • Empty platform mass: 1530 g
  • Max payload mass: 4000 g
  • Payload volume: up to 2U
  • PLT3 platform is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be straight ready for the payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized for the customer.
  • Sample mission code is pre-installed for the customer to be able to run system diagnostics upon delivery of the platform and quick payload integration.
  • Sophisticated mission code can be prepared by NanoAvionics team according to separately agreed terms and conditions.
  • Payload integration service can be performed by NanoAvionics team according to separately agreed terms and conditions.
  • EPSS C1K Propulsion system as an option.

Payload Controler

  • ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
  • Double-precision FPU
  • 1 MB of internal RAM
  • 2 MB of internal FLASH memory
  • 512 KB of FMC connected FRAM
  • 256 MB of external NOR-FLASH for data storage (2 x two die (64 MB each) chips, QSPI)
  • 512 KB of FRAM (SPI) for frequently changing data storage
  • 2 x microSD NAND memory up to 16 GB (SDIO)
  • Integrated RTC with backup power supply
  • On-board PWM drivers for thermal control
  • FreeRTOS
  • In-orbit firmware update
  • CSP, KISS support
  • Self-Diagnostics

Power System

  • Input, output converter efficiency: > 90 %
  • Battery cells balancing
  • Configurable thermal control system
  • Supported data interfaces: CAN, with CSP protocol support, UART
  • Fail-safe design: in case of total microcontroller malfunction EPS will go to emergency mode and selected emergency channels will keep satellite operational

Outputs (Over-current protected):

  • 4 regulated voltage rails: 3.3 V; 5 V; (3 V – 18V configurable)
  • 10 regulated configurable – 3.3 V / 5 V / 3V – 18 V
  • Unregulated with switch: battery voltage 6.4 V – 8.4 V
  • Max channel output current: 3 A
  • Max 3.3 V rail output: 20 W
  • Max 5 V rail output: 20 W
  • Max 3-18 V rail output: 20 W
  • Max unregulated output: 75 W

Inputs:

  • 4 MPPT converters (8 channels) with integrated ideal blocking diodes
  • Voltage: 2.5 – 18 V
  • Max input power per converter: 25 W

Batteries:

  • Standard battery (EPSL): 2 cells, 7.4 V, 3200 mAh, 23 Wh
  • Optional extended battery pack (EPSH): 4 cells, 7.4 V, 6400 mAh, 46 Wh

Flight Computer (Including ADCS functionality)

  • ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
  • FreeRTOS
  • In-orbit firmware update and Self-Diagnostics
  • CSP, KISS support
  • Mission planner with time scheduled script/task execution support
  • Telemetry logging

ADCS sensors and actuators:

  • NanoAvionics Sun Sensors
  • Integrated magnetic and inertial sensors
  • Reaction Wheels System NanoAvionics “SatBus 4RW0”
  • Integrated NanoAvionics Magnetorquers

Attitude control type: 3-axis stabilization

Attitude control accuracy: ± 5°

Stability accuracy: ± 0.5°/s

Attitude maneuver ability: 20 – 60 °/s

Operational modes:

  • Detumble mode
  • Velocity Vector / Nadir pointing mode
  • Sun maximum power tracking
  • Earth target tracking according to geodetic coordinates
  • User-supplied vector tracking

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