LabSat

LabSat is the product of institutions such as Wroclaw University of Science and Technology, Wrocław University of Environmental and Life Sciences, Wroclaw Medical University, and Ludwik Hirszfeld Institute of immunology and Experimental Therapy. SatRevolution provided a platform in the form of a 3U CubeSat bus for the purpose of conducting biological experiments. LabSat will launch into orbit on December 2020 on SpaceX Falcon 9 rocket.
ico-amicalsat-01

CubeSat based science mission

ico-swiatowid-02

Biological science mission to determine the survival of microorganisms in extreme conditions

ico-amicalsat-03

Science joint project with Wrocław University of Science and Technology

Subsystems

Bilogical experiment:

Biological science experiment to determine the survival of microorganisms in extreme conditions.

Command and Data Handling module with following capabilities:

  • Main processor: up to 216MHz, 2MB FLASH
  • Storage memory: from 1GB up to 16GB NAND FLASH
  • External program memory: up to 3MB with hardware Forward Error Correction (possible TMR)
  • Possible payload interfaces: I2C, SPI, UART, RS485, RS422, CAN, USB, Ethernet, DAC/ADC
  • Multiple temperature sensors
  • Working temperatures: -30oC to 65oC
  • Power Supply: independent DC/DC converter
  • Over The Air update

Redundant Low frequency communication module include:

  • Two independent radio transceiver
  • Frequency range: 400-440 MHz (possible reconfiguration on request [120-500 MHz])
  • Transmission data rate 9,6 kb/s
  • RF output power: 30dBm (possible reconfiguration on request)
  • External program memory: up to 1MB with hardware Forward Error Correction
  • Radio Sensitivity: -120dBm
  • Over The Air update

S-band communication module include:

  • S-band operational frequency 2200 – 2290 MHz, 2400-2450 MHz
  • RF output power: 30dBm
  • S-band transmission rate 0,5 Mb/s
  • External program memory: up to 1MB with hardware Forward Error Correction
  • Over The Air update

Platform is equipped with following attitude determination and control subsystems:

  • Advance flight computer
  • 3x magnetorquers
  • Possible 3x reaction wheels
  • Coars sun-sensors
  • Fine sun-sensors
  • 1x magnetometer 3-axis
  • 1x gyroscope 3-axis
  • 1x GPS receiver

Platform allows for the following accuracy:

  • <1 degree of positioning accuracy
  • <1 degree of pointing accuracy

Power management system is based on complex of Energy Harvesting System; Battery Management System; Auxiliary Power System (payload power supply).

  • Peak power 75W
  • System redundancy, autonomous fault handling and recovery
  • Battery supervisory circuit
  • Hardware protection from excessive discharge
  • Hardware MPPT implementation
  • User programable up to 6A maximum battery pack load current
  • Available Power Supply: 1.8V, 3.3V, 5V, 12V and unregulated Battery Voltage

UniBus structure:

  • CNC manufactured of Aluminium 6061, 5083, 6082 alloy
  • Hard anodized and oxidized
  • Up to 2 safety deployment switches and 1 RBF pins
  • Two separation springs
For more information please visit Wrocław University of Sicence and Technology website
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UNITED KINGDOM OFFICE

R71 Rutherford Appleton Laboratory
Harwell Campus
Didcot OPX11 0QX,
Oxfordshire, UK 

POLAND OFFICE

Stabłowicka 147
54-066 Wrocław
Poland

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United States

 

+48 533 325 851
contact@satrevolution.com

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