Microsatellite Bus MP42H - NanoAvionics
Small Satellite
Microsatellite Bus MP42H

Despite decreases in launch costs, the size and weight of a satellite are still very important defining characteristics in the development of a mission or service. The MP42H is NanoAvionics’ smallest and lightest microsatellite bus, ideal for complex communications missions, and comes with an 11″ ESPA-class separation ring for deployment in orbit.

This pre-designed versatile system allows users to focus more on high-value tasks such as payload integration and testing. It can accommodate payloads with a total mass of 35 kg and a maximum footprint of 410(L) x 392(W) x 330(H) mm. Payload height is flexible, as long as the total satellite height does not exceed the launch vehicle’s available volume.

Despite being only slightly larger and heavier than most higher-end nanosatellites, the MP42H can provide far greater mission capabilities and redundancy opportunities. Thanks to the extra avionics volume, better thermal management, and larger payload interface, it offers significantly more capabilities for only a marginal price increase.

NanoAvionics offers three MP42H microsatellite standard performance configurations – Light, Mid, and Max – providing options that best match customers’ payload mission objectives and budget.

As with all of NanoAvionics’ proven platforms, the MP42H is a highly modular system. Configurable subsystems and operational protocols enable faster setup. The system also has a sample mission code pre-installed so that testing can commence immediately upon delivery.

The MP42H bus is well-suited for single-satellite missions or as the standardized platform for an entire constellation. It is highly versatile and optimized for remote sensing, high data throughput, and complex communications missions, emergency communications, and fundamental research missions.

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MP42H 11" Light
Base performance
MP42H 11" Mid
Fast downlink
MP42H 11" 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
100 W
29 kg
410 x 392 x 330 mm
75 kg
1 Mbps / 3 Mbps
4.31° (1σ)
4.40° (1σ)
11"
98 W
29 kg
410 x 392 x 330 mm
75 kg
1 Mbps / 200 Mbps
4.31° (1σ)
4.40° (1σ)
11"
94 W
29 kg
410 x 392 x 330 mm
75 kg
1 Mbps / 200 Mbps
0.04° (1σ)
0.08° (1σ)
11"
Base performance
Available Payload Power (Sun Tracking)
100 W
Available Payload Mass
29 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.
410 x 392 x 330 mm
Max Allowable S/C Mass
75 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
11"
Fast downlink
Available Payload Power (Sun Tracking)
98 W
Available Payload Mass
29 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.
410 x 392 x 330 mm
Max Allowable S/C Mass
75 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
11"
High pointing accuracy
Available Payload Power (Sun Tracking)
94 W
Available Payload Mass
29 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.
410 x 392 x 330 mm
Max Allowable S/C Mass
75 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
11"
Why NanoAvionics Cubesats/Microsatellites?
  • Driving key small satellite developments for over 10 years
  • Trusted partner by 142+ customers
  • 92,3% full mission lifetime success rate (7,7% 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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