What is the average thrust of a microsatellite? | Q & A

Microsatellites, which typically range in mass from 10 to 100 kilograms, have varying thrust requirements depending on their specific mission objectives, propulsion systems, and desired maneuvers. Here are some general insights into the average thrust for microsatellites:

• Electric Propulsion Systems: Many microsatellites use electric propulsion (e.g., ion thrusters, Hall effect thrusters) due to their high efficiency and low fuel consumption. These systems provide relatively low thrust, typically ranging from a few millinewtons (mN) to a few tens of millinewtons. For example:

  • Ion Thrusters: 0.1 to 20 mN
  • Hall Effect Thrusters: 10 to 100 mN

• Cold Gas Thrusters: Often used for attitude control or small delta-v maneuvers, these thrusters provide low thrust, usually in the range of 0.1 to 1 Newton (N).

• Chemical Propulsion Systems: Some microsatellites use small chemical propulsion systems for larger maneuvers or orbital adjustments. These can provide higher thrust, typically in the range of 1 to 10 Newtons.

• Attitude Control: For fine-tuning the orientation of the microsatellite, thrust levels are usually very low, often provided by electric or cold gas thrusters in the millinewton range.
• Orbital Maneuvers: For changing or maintaining orbit, the thrust requirement depends on the specific delta-v (change in velocity) needed. This can range from millinewtons to a few Newtons.
• Deorbiting: For end-of-life disposal, higher thrust may be required to lower the orbit rapidly, often achieved by chemical propulsion systems providing thrust in the Newton range.

• Cubesats: A common type of microsatellite, cubesats often use electric propulsion systems like the Busek BHT-200 Hall thruster, which provides around 12 mN of thrust.
• NanoSat Propulsion: Systems like the Enpulsion IFM Nano Thruster provide thrust in the range of 1 to 5 mN, suitable for small delta-v maneuvers.

The average thrust for a microsatellite can vary widely based on the propulsion system and mission requirements. Electric propulsion systems typically offer thrust from a few millinewtons to tens of millinewtons, while chemical propulsion systems can provide thrust from 1 to 10 Newtons for more significant maneuvers. For specific mission needs, thrust requirements should be tailored to the satellite's objectives and operational constraints.