ECAPS's 50N HPGP Thruster is designed for attitude, trajectory, and orbit control of larger satellites, including geostationary satellites, or launch vehicle applications. This thruster is currently in development and looking for partners to bring the prior work into fruition.

  • Propellant loading is simple, fast and avoids the cost associated with loading hydrazine. Allows the operator to spend less time on ground operations and more time on space operations.
  • ‘Fuel at the factory’ – be ready for launch vehicle integration upon arrival at the launch pad. Eliminates significant time and cost from lengthy pre-launch campaigns.
  • Non-toxic propellant is suitable for a new class of responsive small satellite launchers, where handling hazardous hydrazine may impede operations or where fully equipped hydrazine processing facilities may be non-existent at the launch site.
  • Higher performance over hydrazine allows for more payload or longer mission durations.
  • Allows for more secondary or ‘piggy-back’ launch opportunities, especially missions where there is concern about the hazards of hydrazine and its risks to the primary payload.
  • Allows for more agile mission profiles than electric propulsion. Spacecraft take significantly less time to execute maneuvers and orbit changes.

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Last updated: 2024-02-05

50N HPGP Thruster




inlet pressure range
5 to 26 bar
thrust range
12.5 to 50 N
Nozzle Expansion Ratio
Steady State Isp
2385 to 2500 Ns/kg
specific impulse
243 to 255 s
Density Impulse
2957 to 3100 Ns/L
minimum impulse bit
< 2.5 N s
327 mm
2.1 kg
Nominal Reactor Pre-heating Voltage
28 VDC
Regulated Reactor Pre-heating Power
75 to 100 W
2000 (Target Life – Qual. Level)
160 (Demonstrated Life)
Propellant Throughput
50 (Target Life – Qual. Level)
1.7 (Demonstrated Life)
Longest Continuous Firing
25 (Target Life – Qual. Level)
10 (Demonstrated Life)
Accumulated Firing Time
1 (Target Life – Qual. Level)
45 (Demonstrated Life)
Firing Sequences
100 (Target Life – Qual. Level)
12 (Demonstrated Life)


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