CubeSat Propulsion System EPSS | NanoAvionics
SmallSat Propulsion System EPSS

SmallSat Propulsion System EPSS

The minimum order quantity for this subsystem is 5 pieces.

NanoAvionics is the first aerospace company ready to offer a high-performance and environment-friendly CubeSat propulsion system, also suitable for small satellites. The system has the potential to unlock massive relaunch savings for satellite operators by an estimated 80%.

The propulsion system is modular in design, permitting integration with multiple present and future small satellite platforms on the market. The system is designed to be easily scaled to optimize for the client mission by adjusting the volume of the tank to accommodate different propellant quantity needs.

This system is fueled with ADN-based monopropellant, which has up to 6% higher specific impulse and 24% higher energy density as compared to the hydrazine employed systems, permitting significant levels of thrust to be stored within a relatively small storage volume. In addition, EPSS allows a high thrust-to-volume-to-weight ratio at a very low power budget requirement making it a very competitive and proven solution, even when compared with the electric (high Isp) propulsion.

As ADN-based propellant is “green”, its usage contributes to ESA’s and NASA’s clean space initiatives. Components such as valves, fuel tanks, propellant management system, and high-performance thrusters were designed, manufactured. and supplied by NanoAvionics’ partners – globally trusted aerospace companies.

The first in-orbit test was performed during LituanicaSAT-2 mission.

Drag to sides
Request information

The minimum order quantity for this subsystem is 5 pieces.

NanoAvionics is the first aerospace company ready to offer a high-performance and environment-friendly CubeSat propulsion system, also suitable for small satellites. The system has the potential to unlock massive relaunch savings for satellite operators by an estimated 80%.

The propulsion system is modular in design, permitting integration with multiple present and future small satellite platforms on the market. The system is designed to be easily scaled to optimize for the client mission by adjusting the volume of the tank to accommodate different propellant quantity needs.

This system is fueled with ADN-based monopropellant, which has up to 6% higher specific impulse and 24% higher energy density as compared to the hydrazine employed systems, permitting significant levels of thrust to be stored within a relatively small storage volume. In addition, EPSS allows a high thrust-to-volume-to-weight ratio at a very low power budget requirement making it a very competitive and proven solution, even when compared with the electric (high Isp) propulsion.

As ADN-based propellant is “green”, its usage contributes to ESA’s and NASA’s clean space initiatives. Components such as valves, fuel tanks, propellant management system, and high-performance thrusters were designed, manufactured. and supplied by NanoAvionics’ partners – globally trusted aerospace companies.

The first in-orbit test was performed during LituanicaSAT-2 mission.

  • Main Functions:

    The Enabling Propulsion System for Small Satellites (EPSS) is a versatile system allowing nano-satellites to perform:

    • Constellation deployment and formation flights;
    • Drag compensation and orbit maintenance;
    • Orbital maneuvering, including Hohmann transfer;
    • Synchronization and positioning of communication equipment and payload instruments;
    • De-orbiting at the end of the mission and other functions.
  • Main Technical Specifications:

    These specifications apply only to the C2 configuration. C1.5 and C3 configurations specifications can be provided on request.

    • System Name – EPSS C2
    • Propulsion System Size (width x depth x height), mm – 100 x 100 x 200
    • Lead Time – 12-14 months
    • Propellant Type – Ammonium Dinitramide (ADN) Blend
    • Thrust (N) per Thruster – 1N BOL to 0.25N EOL
    • Propulsion System Dry Mass (kg) – 1.8
    • Propulsion System Wet Mass (kg) – 2.6
    • Propulsion System Rad tolerance (rads) – 20k
    • Propulsion System Vibration (Grms) – 14.1 qualification
    • Sub – System Data Interface  – CAN / UART / RS422
    • Sub – System Operating Voltage for Heaters and Valves (V) – 12
    • System Telemetry Logic Voltage TLM (V) – 3.3
    • Mission BOL Pressure (Bar) – 25
    • Mission EOL Pressure (Bar) – 5.5
    • Propellant Mass (kg) – 0.8
    • No. of Thrusters – 1
    • Average Specific Impulse (s) – 220
    • Maximum Total Impulse (N.s) – > 1700
    • Mass flow (g/s) – 0.5 BOL to 0.12 EOL
  • Configuration Options:

    CubeSat Propulsion EPSS C1.5 (1.5U)

    CubeSat Propulsion EPSS C2 (2U)

    CubeSat Propulsion EPSS C3 (3U)

  • Flight Heritage:

    Multiple missions, the latest:

    CubeSat Propulsion EPSS C1 (1U) – 2019.04.01 M6P