Lunar Flashlight Propulsion System

VACCO’s green mono-propellant Micro Propulsion System (MiPS) provides a highly reliable solution for a fully self-contained CubeSat attitude control and main propulsion system. JPL’s Lunar Flashlight program will use VACCO’s MiPS configured for ADN green propellant to perform its Lunar surveying mission.

The VACCO Lunar Flashlight MiPS is approximately 3U in volume and uses four 100 mN thrusters to develop 3,320 N-sec of total impulse that provides 237 m/s of delta-V for a 14 kg CubeSat. Each thruster independently operates to perform both delta-V and ACS maneuvers controlled by an integrated microprocessor controller.


  • Integral titanium fluid control manifold and low friction, space grade valves
  • All welded tank construction contains 2 kg of propellant
  • Integrated microcontroller and RS-422 interface enable high-level commands from the host spacecraft
  • Low power with < 1 Watt for health and status monitoring
  • Easily configured for different mono-propellants
    • ADN green (LMP-103S)
    • Air Force green (AF-M315E)
  • Performance density: 969 N-sec/L

Lunar Flashlight Propulsion System Datasheet pdf-icon

Operating Parameters

Propellant LMP-103S (ADN)
Total Impulse @10°C 3,320 N-s
MDP 29.1 Bar (422 psia)
Dry Mass 3.0 kg Max
Proof Pressure 43.6 Bar (633 psia)
Wet Mass 95% Fill @ 10°C 5.0 kg Max
Burst Pressure 58.2 Bar (844 psia)
Operating Voltage For Telemetry 5±0.25 VDC
Internal Leakage BOL 1.0 x 10-4 sccs GHe
Operating Voltage For Heaters & Valves 9.5-12.6 VDC
Internal Leakage EOL 1.0 x10-3 sccs GHe
Standby Power 10 W Max
External Leakage ≤1.0 x 10-6 sccs GHe
Warmup Power 35 W Max
Operating Temp 10°C to 40°C
Thruster Operating Power (4 thrusters) 15 W Max
Non-Operating Temp -34°C to 60°C
Data Interface RS-422
Performance characteristics are based on customer requirements. As such, they are not representative of component capabilities or limitations.

Envelope Drawing


Flow Schematic