ROADMAP

SatRevolution is constantly developing new products, which can be seen in the subsystems and platforms that we manufacturing. This what make us different from other companies of the New Space is the fact that we specialize in Earth Observation.

Subsystems roadmap

  • 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
  • 3x magnetorquers; Possible
  • 3x reaction wheels;
  • Coars sun-sensors;
  • Fine sun-sensors;
  • 1x magnetometer 3-axis;
  • 1x gyroscope 3-axis;
  • 1x GPS receiver;
  • <1 degree of positioning accuracy;
  • <1 degree of pointing accuracy

Subsystem for control of payload power supply:

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

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 roadmap

  • 6U Cubesat structure satellite bus,
  • CNC machined Aluminium 6061, 5083, 6082 alloy;
  • Up to 4U of payload capacity;
  • Payload interfaces avaiable: I2C, SPI, UART, RS485, RS422, CAN, USB, Ethernet, DAC/ADC;
  • 50W peak payload power,
  • 75W total peak power;
  • Avaiable power supply: 1.8V, 3.3V, 5V, 12V;
  • Capacity of battery: 54.6 Wh on pack;
  • Additional battery pack available as a option;
  • Command & data handling module with payload management system;
  • ADCS: <1 degree of pointing accuracy; 3x magnetorquers; 3x reaction wheels; 2x sun sensors; 3x magnetometer in 3 axis; 3x gyroscope in 3 axis; 1x GPS receiver;
  • Redundant UHF communication system for command telemetry; frequency range: 400-440MHz; RF output power 30dBm; transmission data rate 9,6kbps;
  • S-band communication system for data downlink; S-band range 2200-2290MHz or 2400-2450MHz; RF output power 30dBm;
  • Flight software; payload management software;
  • Qualification testing;
  • Propulsion system (optional, not included in the price)
  • 12U Cubesat structure satellite bus,
  • CNC machined Aluminium 6061, 5083, 6082 alloy;
  • Up to 8U of payload capacity;
  • Payload interfaces avaiable: I2C, SPI, UART, RS485, RS422, CAN, USB, Ethernet, DAC/ADC;
  • 120W peak payload power,
  • 150W total peak power;
  • Avaiable power supply: 1.8V, 3.3V, 5V, 12V; up to 36V custom;
  • Capacity of battery: 109.2 Wh on pack;
  • Additional battery pack available as a option;
  • Command & data handling module with payload management system;
  • ADCS: <1 degree of pointing accuracy; 3x magnetorquers; 3x reaction wheels; 4x sun sensors; 3x magnetometer in 3 axis; 3x gyroscope in 3 axis; 1x GPS receiver;
  • Redundant UHF communication system for command telemetry; frequency range: 400-440MHz; RF output power 30dBm; transmission data rate 9,6kbps;
  • S-band communication system for data downlink; S-band range 2200-2290MHz or 2400-2450MHz; RF output power 30dBm;
  • X-Band transmission optional;
  • Flight software; payload management software;
  • Qualification testing; Propulsion system
  • GSD 1m or less;
  • Custom made lens and CMOS camera;
  • B, G, R, NIR channels;
  • Imagery on board analyzing system based on AI

Main Goal

In addition to the goals outlined above, our main goal is to establish the first Polish Earth Observation constellation. REC – Real-time Earth-observation Constellation is already under development. We have presented the REC Roadmap below.

REC Roadmap

2019 Q2-Q3
Phase A
DeploScope’s SRC PAS design proposal granted in March. NanoBus in orbit demonstration (as Światowid’s base in mid July)
2019 Q2-Q3
2023 Q2
Phase B
ScopeSat prototype full in orbit demo. 8 ScopeSats - 10 days revisit time
2023 Q2
2024 Q1
Phase C
16 ScopeSats in orbit – 1 day revisit time
First constellation’s iteration
2024 Q1
2024 Q4
Phase D
66 ScopeSats in orbit – 4 h revisit time
Second constellation’s iteration
2024 Q4
2028 Q1
Phase E
1024 ScopeSats in orbit – 30 min revisit
Final constellation’s iteration
2028 Q1

How to reach us

UNITED KINGDOM OFFICE

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

POLAND OFFICE

Stabłowicka 147
54-066 Wrocław
Poland

U.S.A. OFFICE

388 Market Street (Suite 1300)
San Francisco, CA 94111
United States

 

+48 533 325 851
contact@satrevolution.com