01 05
CubeSat Propulsion System EPSS

CubeSat Propulsion System EPSS

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 high thrust-to-volume-to-weight ratio at very low power budget

required making it very competitive and practically 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

CubeSat Propulsion System EPSS

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 high thrust-to-volume-to-weight ratio at very low power budget

required making it very competitive and practically 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 1U configuration. 2U and 3U configuration specification provided on request.

    • Thruster Name – EPSS C1
    • Propulsion System Size – 1U
    • Thruster Type – Chemical
    • Lead Time – 12-14 months
    • Propellant Type – Ammonium Dinitramide (ADN) Blend
    • Thrust (N) per Thruster – 0.1
    • Propulsion System Power – Monitoring (W) – 0.191
    • Propulsion System Power – Preheat (W) – 8
    • Propulsion System Power – Firing (W) (all thrusters) – 1.7
    • Propulsion System Dry Mass (kg) – 0.8
    • Propulsion System Wet Mass (kg) – 1.2
    • Propulsion System Rad tolerance (rads) – 20k
    • Propulsion System Vibration (Grms) – 14.1 qualification
    • Sub – System Data Interface (e.g. RS422) – CAN / UART (umbilical)
    • Sub – System Operating Voltage for Heaters and Valves (V) – 12
    • System Telemetry Logic Voltage TLM (V) – 3.3
    • Propellant Storage Configuration – Barrier-separated constant pressure gas pressurized
    • Mission Design Pressure (Bar) – 10
    • Proof Pressure (Bar) – 32
    • Burst Pressure (Bar) – 36
    • Propellant Mass (kg) – 0.33
    • No. of Thrusters – 1
    • Specific Impulse (s) – 200
    • Total Impulse (N.s) – 650
    • Mass flow (kg/s) – 5.10E-05
    • Min valve operating time (s) – 2.00E-02
  • Configuration Options:

    CubeSat Propulsion EPSS C1 (1U)

    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