Microsatellite Bus MP42D - NanoAvionics
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Small Satellite

Microsatellite Bus MP42D

The MP42D small satellite bus is NanoAvionics’ largest and heaviest microsatellite offering, ideal for demanding space applications. With a maximum payload footprint of 730(L) x 730(W) x 600(H) mm, and a 24″ ESPA-class separation ring for orbital deployment, it can support payloads of up to 100 kg.

As with all of our standard microsatellite buses, MP42D has three performance configurations – Light, Mid, and Max – to match customers’ payload mission requirements and accelerate payload integration.

The MP42D can also be equipped with an optional propulsion system to perform high total impulse maneuvers for orbit synchronization and atmospheric drag compensation, which allows the satellite to extend its orbital lifetime and adapt to changing mission objectives.

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MP42D 24" Light
Base performance
MP42D 24" Mid
Fast downlink
MP42D 24" Max
High pointing accuracy
Available Payload Power (Sun Tracking)
Available Payload Mass
Available Payload Volume
Given values represents Length, Width, Height. Payload height is dependent on the launch vehicle allowable volume and shall be confirmed with KNA in advance.
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.
Deployment Ring
240 W
100 kg
730 x 730 x 600 mm
200 kg
1 Mbps / 3 Mbps
4.31° (1σ)
4.40° (1σ)
24"
237 W
100 kg
730 x 730 x 600 mm
200 kg
1 Mbps / 200 Mbps
4.31° (1σ)
4.40° (1σ)
24"
233 W
100 kg
730 x 730 x 600 mm
200 kg
1 Mbps / 200 Mbps
0.04° (1σ)
0.08° (1σ)
24"
Base performance
Available Payload Power (Sun Tracking)
240 W
Available Payload Mass
100 kg
Available Payload Volume
Given values represents Length, Width, Height. Payload height is dependent on the launch vehicle allowable volume and shall be confirmed with KNA in advance.
730 x 730 x 600 mm
Max Allowable S/C Mass
200 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)
Deployment Ring
24"
Fast downlink
Available Payload Power (Sun Tracking)
237 W
Available Payload Mass
100 kg
Available Payload Volume
Given values represents Length, Width, Height. Payload height is dependent on the launch vehicle allowable volume and shall be confirmed with KNA in advance.
730 x 730 x 600 mm
Max Allowable S/C Mass
200 kg
Data Rates (Uplink/Downlink)
1 Mbps / 200 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)
Deployment Ring
24"
High pointing accuracy
Available Payload Power (Sun Tracking)
233 W
Available Payload Mass
100 kg
Available Payload Volume
Given values represents Length, Width, Height. Payload height is dependent on the launch vehicle allowable volume and shall be confirmed with KNA in advance.
730 x 730 x 600 mm
Max Allowable S/C Mass
200 kg
Data Rates (Uplink/Downlink)
1 Mbps / 200 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)
Deployment Ring
24"
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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