NASA C-POD Micro Propulsion System
VACCO Industries
The NASA C-POD Micro Propulsion System is a self-contained reaction control module designed for 3U CubeSats, providing precise attitude control and rendezvous/proximity operations using non-toxic R236fa propellant.
Typed specifications28 values
Discloses 8 of 11 fields engineers filter by in this category (category median 3).
- Propulsion family
- cold-gas datasheet p.1
- Mass
- 1.33 kg estimated weight with propellant · datasheet p.1 1.33 kg with Propellant
- Thrust
- 10 mN Nominal Continuous Thrust · datasheet p.1 10 mN nom. · nominal continuous thrust, +/- 2 mN
- Specific impulse
- 40 s datasheet p.1
- Total impulse
- 174 N·s datasheet p.1
- Propellant
- R236fa datasheet p.1
- Supply voltage
- 9–12.6 V datasheet p.1
- Power consumption
- 5 W Max Power (2 Thrusters) · datasheet p.1 0.25 W Max Standby Power Consumption | 5 W max · max power, 2 thrusters | 0.25 W max · standby
- Data interface
- RS-422 datasheet p.1
- Operating temperature
- -20–60 °C datasheet p.1
- Thruster technology
- cold gas datasheet p.1
- Thrusters in the unit
- 8 datasheet p.1
- Volume
- 3 U designed to occupy the center of · datasheet p.1
- Min impulse bit
- 0.5 mN·s datasheet p.1
- Feed / tank pressure
- 6.89 bar MDP · datasheet p.1 6.89 bar max · MDP
- Power at thrust
- 5 W max · 2 thrusters · datasheet p.1
- Time to thrust
- 10 s max · thruster valve response <10 mSec · datasheet p.1
- Survival temperature
- -34–60 °C datasheet p.1 -34–60 °C non-operating
- Satellite class
- CubeSat center of a 3U CubeSat · datasheet p.1
- Power processing unit included
- yes datasheet p.1
- Ignition or start
- none (cold gas) datasheet p.1
Each value is typed with its unit and measurement condition and cites the datasheet page it was taken from. Nothing is guessed: a field that is absent here has not been published by the manufacturer. machine-extracted ✓ checked by NewSpace Market ✓ manufacturer confirmed by the manufacturer.
As published by the supplier10 lines, in the manufacturer's own wording
- Operating temperature range
- 0°C to 60°C
- Total impulse
- 186 N-sec
- Operating voltage
- 9 to 12.6 vdc
- Nominal continuous thrust
- 10 mN +/- 2 mN
- Max standby power consumption
- 0.25 watts
- Minimal impulse bit
- 0.50 mN-sec
- Max steady-state power
- 5 watts
- Thruster valve response
- <2 mSec
- Specific impulse (Isp)
- 40 s
- Estimated weight with propellant
- 1,244 grams
About
VACCO’s NASA C-POD Micro Propulsion System is a self-contained unit engineered to fit within the center of a 3U CubeSat. It features a total of eight thrusters, arranged in groups of two at each of the four corners of the module, enabling precise rendezvous and proximity operations, as well as full CubeSat attitude control. The system utilizes R236fa propellant, which self-pressurizes across its normal operating temperature range, contributing to range safety. This smart system is designed to interface with the spacecraft via an RS422 data bus for command and control. The NASA C-POD Micro CubeSat Propulsion System can be scaled down from 0.8U to meet specific mission and payload requirements. Key features include inherently safe non-toxic R236fa propellant, two seals to prevent propellant leakage, eight fast-response, low-power 10 mN cold gas thrusters, an integral electronic controller, aluminum construction, and a lightweight design that ensures destruction during re-entry. It also incorporates a proportional heater and temperature sensor for precise control of propellant pressure.
Documentation
Need the full ICD, test reports or a specific revision? Ask the supplier directly.