ECAPS's 22N HPGP Thruster is designed for attitude, trajectory and orbit control of larger satellites and for systems such as propulsive payload adaptor rings.

  • Non-toxic propellant makes for easier and less costly integration on secondary or ‘piggy-back’ missions.
  • 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.
  • Non-toxic propellant makes payload adaptor rings suitable for a new class of small satellite launchers, where handling hazardous hydrazine may impede operations or where fully equipped hydrazine processing facilities may be non-existent.
  • 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 capable missions than spacecraft without propulsion.
  • 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

22N HPGP Thruster




inlet pressure range
5.5 to 24 bar
thrust range
5.5 to 22 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
< 0.44 N s
260 mm
1.1 kg
Nominal Reactor Pre-heating Voltage
28 VDC
Regulated Reactor Pre-heating Power
25 to 50 W
50000 (Target Life – Qual. Level)
26481 (Demonstrated Life)
Propellant Throughput
150 (Target Life – Qual. Level)
53 (Demonstrated Life)
Longest Continuous Firing
45 (Target Life – Qual. Level)
38 (Demonstrated Life)
Accumulated Firing Time
7.6 (Target Life – Qual. Level)
3 (Demonstrated Life)
Firing Sequences
350 (Target Life – Qual. Level)
282 (Demonstrated Life)


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