1 N HPGP Thruster
ECAPS
- Thrust Range:
- 5.5 to 22 N
- Propellant:
- LMP-103S
- Mass:
- 1.0 Kg
- Length:
- 260 mm
- Flow Control Valve Type:
- Solenoid
- Pull-in Voltage:
- 28 (+/- 4) VDC
- Holding Voltage:
- 10 (+/- 1) VDC
- Nominal Reactor Pre-heating Voltage:
- 28 VDC
- Regulated Reactor Pre-heating Power:
- 36 to 50 W
- Minimum Impulse Bit:
- < 0.44 Ns
- Pulses:
- 50,000 (qualification level)
- Propellant Throughput:
- 150 kg (qualification level)
- Longest Continuous Firing Time:
- 45 mins (qualification level)
- Accumulated Firing Time:
- 3 hrs (qualification level)
- Firing Sequences:
- 282 (qualification level)
The 22 N High Performance Green Monopropellant (HPGP) thruster enables high thrust apogee, reaction control and proximity operations maneuvering medium-large spacecraft and kick stages.
The 22 N HPGP Thruster also enables high thrust delta-V maneuvers and AOCS for small-medium class spacecraft and reaction control for large spacecraft.
The thruster operates on LMP-103S low-toxicity monopropellant with 1.3C the density-Isp of hydrazine. Additionally, LMP-103S offers up to 72% cheaper spacecraft loading as compared to hydrazine, reducing the total life-cycle cost of the mission.
The propellant is long term storable (>15 years) and enables "fuel at the factory" for rapid response satelliltes. Over 31 satellites are presently flying HPGP technology (as of 2024).
Mechanical Interface:
22 N HPGP Thruster
ECAPSThe 22 N High Performance Green Monopropellant (HPGP) thruster enables high thrust apogee, reaction control and proximity operations maneuvering medium-large spacecraft and kick stages.
The 22 N HPGP Thruster also enables high thrust delta-V maneuvers and AOCS for small-medium class spacecraft and reaction control for large spacecraft.
The thruster operates on LMP-103S low-toxicity monopropellant with 1.3C the density-Isp of hydrazine. Additionally, LMP-103S offers up to 72% cheaper spacecraft loading as compared to hydrazine, reducing the total life-cycle cost of the mission.
The propellant is long term storable (>15 years) and enables "fuel at the factory" for rapid response satelliltes. Over 31 satellites are presently flying HPGP technology (as of 2024).
Mechanical Interface:
- Thrust Range:
- 5.5 to 22 N
- Propellant:
- LMP-103S
- Mass:
- 1.0 Kg
- Length:
- 260 mm
- Flow Control Valve Type:
- Solenoid
- Pull-in Voltage:
- 28 (+/- 4) VDC
- Holding Voltage:
- 10 (+/- 1) VDC
- Nominal Reactor Pre-heating Voltage:
- 28 VDC
- Regulated Reactor Pre-heating Power:
- 36 to 50 W
- Minimum Impulse Bit:
- < 0.44 Ns
- Pulses:
- 50,000 (qualification level)
- Propellant Throughput:
- 150 kg (qualification level)
- Longest Continuous Firing Time:
- 45 mins (qualification level)
- Accumulated Firing Time:
- 3 hrs (qualification level)
- Firing Sequences:
- 282 (qualification level)
The 22 N High Performance Green Monopropellant (HPGP) thruster enables high thrust apogee, reaction control and proximity operations maneuvering medium-large spacecraft and kick stages.
The 22 N HPGP Thruster also enables high thrust delta-V maneuvers and AOCS for small-medium class spacecraft and reaction control for large spacecraft.
The thruster operates on LMP-103S low-toxicity monopropellant with 1.3C the density-Isp of hydrazine. Additionally, LMP-103S offers up to 72% cheaper spacecraft loading as compared to hydrazine, reducing the total life-cycle cost of the mission.
The propellant is long term storable (>15 years) and enables "fuel at the factory" for rapid response satelliltes. Over 31 satellites are presently flying HPGP technology (as of 2024).
Mechanical Interface:
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