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CubeSat Propulsion EPSS

CubeSat Propulsion “EPSS” – Green Chemical Propulsion System

NanoAvionics has developed TRL-7 (Technology Readiness Level) level prototype of a miniaturized, high performance, environmentally-friendly CubeSat propulsion system, also suitable for satellites up to 150 kg in mass. This system is fueled by an ADN-based mono-propellant which has up to a 6% higher specific impulse and 24% higher energy density as compared to the hydrazine employed systems. Also, it is permitting significant levels of thrust to be stored within a relatively small storage volume. An ADN-based propellant is “green” and its usage contributes to ESA’s and NASA’s clean space initiatives.

The upcoming product will be scalable according to the client mission requirements. It will be compatible with the CubeSat standard also suitable for satellites below 150 kg. It will be the first complete, harmonized, plug and play propulsion system for satellites available in the market.

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CubeSat Propulsion “EPSS” – Green Chemical Propulsion System

NanoAvionics has developed TRL-7 (Technology Readiness Level) level prototype of a miniaturized, high performance, environmentally-friendly CubeSat propulsion system, also suitable for satellites up to 150 kg in mass. This system is fueled by an ADN-based mono-propellant which has up to a 6% higher specific impulse and 24% higher energy density as compared to the hydrazine employed systems. Also, it is permitting significant levels of thrust to be stored within a relatively small storage volume. An ADN-based propellant is “green” and its usage contributes to ESA’s and NASA’s clean space initiatives.

The upcoming product will be scalable according to the client mission requirements. It will be compatible with the CubeSat standard also suitable for satellites below 150 kg. It will be the first complete, harmonized, plug and play propulsion system for satellites available in the market.

  • General Features

    Components such as thruster, valves, fuel tanks and the propellant management system were designed and manufactured solely in Europe.

    The developed prototype has been tested during the LituanicaSAT-2 satellite mission providing required technical information in order to reach TRL7 level and further develop a commercial product.

  • Applications:
    • Orbital missions such as Earth Observation
    • Communication
    • Accurate weather forecasting
    • Constellation deployment and formation flights
    • Drag compensation and orbit maintenance
    • Interplanetary missions and many other new small satellite applications
  • Performance:
    • Propellant: ADN Blend
    • Nominal Thrust: 100 mN
    • Isp Vacuum: 225 s
    • Min Impulse Bit: 0.002 Ns
    • Min Opening Time Control Valve: 3 ms
    • Propellant Throughput: 1 kg
    • System pressure: 10 Bar
    • Hot Ramp Up / Tail Off: < 50 ms / < 100 ms
    • Chamber Temperature: < 1600 °C
    • Preheat Temperature / Time: 380 °C / 300-500 s
    • Power Consumption (Idle / Peak / Operation): 0.05 W / 5-7.5 W  / 4.5 W
    • Form Factor: 1U