8U CubeSat / Nanosatellite M8P - NanoAvionics
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CubeSat

8U CubeSat / Nanosatellite M8P

NanoAvionics offers the M8P, a 8U CubeSat in three standard configurations — Light, Mid, and Max — to match your payload mass, mission objectives, and budget. This standardised platform, when compared to a standard 6U CubeSat bus, allows for more payload volume and higher duty cycles, thanks to its larger solar panels, all for only a marginal cost increase.

The Light configuration provides base performance for missions such as IoT communications or basic technology demonstrations in low Earth orbit. In contrast, the Mid configuration adds a higher throughput data link system to the package. The Max configuration expands the capabilities of the Mid offering with a star tracker, making it ideal for Earth observation and other applications requiring high pointing accuracy. Each standard configuration can be paired with an optional propulsion system for high total impulse maneuvers.

Our 8U CubeSats can be deployed in orbit using the top half of a 16U CubeSat dispenser, readily available from one of our partners.

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M8P Light
Base performance
M8P Mid
Fast downlink
M8P Max
High pointing accuracy
Available Payload Power (Sun Tracking)
Available Payload Mass
Available Payload Mass With Propulsion
Available Payload Volume
Available Payload Volume With Propulsion
Max Allowable S/C Mass
Data Rates (Uplink/Downlink)
Absolute Knowledge Error
The AKE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
Absolute Performance Error
The APE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
29.5 W
6.5 kg
5.5 kg
5 U
4 U
16 kg
1 Mbps / 3 Mbps
4.31° (1σ)
4.40° (1σ)
26.5 W
6 kg
5 kg
4.5 U
3.5 U
16 kg
1 Mbps / 80 Mbps
4.31° (1σ)
4.40° (1σ)
24.5 W
6 kg
5 kg
4.5 U
3.5 U
16 kg
1 Mbps / 80 Mbps
0.04° (1σ)
0.08° (1σ)
Base performance
Available Payload Power (Sun Tracking)
29.5 W
Available Payload Mass
6.5 kg
Available Payload Mass With Propulsion
5.5 kg
Available Payload Volume
5 U
Available Payload Volume With Propulsion
4 U
Max Allowable S/C Mass
16 kg
Data Rates (Uplink/Downlink)
1 Mbps / 3 Mbps
Absolute Knowledge Error
The AKE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
4.31° (1σ)
Absolute Performance Error
The APE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
4.40° (1σ)
Fast downlink
Available Payload Power (Sun Tracking)
26.5 W
Available Payload Mass
6 kg
Available Payload Mass With Propulsion
5 kg
Available Payload Volume
4.5 U
Available Payload Volume With Propulsion
3.5 U
Max Allowable S/C Mass
16 kg
Data Rates (Uplink/Downlink)
1 Mbps / 80 Mbps
Absolute Knowledge Error
The AKE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
4.31° (1σ)
Absolute Performance Error
The APE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
4.40° (1σ)
High pointing accuracy
Available Payload Power (Sun Tracking)
24.5 W
Available Payload Mass
6 kg
Available Payload Mass With Propulsion
5 kg
Available Payload Volume
4.5 U
Available Payload Volume With Propulsion
3.5 U
Max Allowable S/C Mass
16 kg
Data Rates (Uplink/Downlink)
1 Mbps / 80 Mbps
Absolute Knowledge Error
The AKE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
0.04° (1σ)
Absolute Performance Error
The APE values are reached if the satellite angular velocity does not exceed 0.6 deg/s. The ADCS performance is impacted if this angular velocity is exceeded.
0.08° (1σ)
Why NanoAvionics Cubesats/Microsatellites?
  • Driving key small satellite developments for over 10 years
  • 50+ Satellites in orbit with 300+ in development
  • 94,44% full mission lifetime success rate (5,56% partial success) compared to 72,69% (15,4% partial) industry average
  • Rigorous product and quality assurance processes with heavy focus on radiation testing
  • Truly agnostic manufacturer, not competing with our customers by becoming a data provider
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Highlighted missions
Onera Flylab
Client Onera
NanoAvionics will provide 2 satellite buses for the Onera FlyLab mission is. As its name suggests, a true “Flying Laboratory” composed of two satellites, FlyLab-1 (8U) and FlyLab-2 (6U) will use a fine attitude control system to perform formation flying in very close proximity and use thermal and visible light cameras for Earth observation, as well as conduct research using VHF and L-band software-defined radios (SDR).
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IBS CLOVESat-1
Client Institute for Basic Science
CLOVESat-1 is an 8U CubeSat for the world’s first long-term planetary science campaign using a series of satellites to investigate the atmospheric changes of Venus from low Earth orbit over a 15-year period. It will carry instruments covering ultraviolet to near-infrared, which will work in tandem with ground-based observatories and upcoming NASA and ESA Venus missions, DAVINCI, VERITAS, and EnVision.
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