Microsatellite Bus MP42 - NanoAvionics
Small Satellite
Microsatellite Bus MP42

Small satellites offer high performance and reliability for various space applications, such as high-resolution Earth Observation, other remote sensing services, and complex communications missions, such as space-based internet services. NanoAvionics’ MP42 mid-range microsatellite bus, uses a 15″ ESPA-class separation ring and can accommodate payloads with a maximum mass of 70 kg and a footprint of 625 x 460 x 370 mm(h)* mm. This payload volume suits deployable antennas, optical imagers, and other structures.

As part of the company’s ongoing program to deliver some of the most cost-effective commercially available modular microsatellite buses that facilitate efficient payload integration and orbital deployment, the MP42 offers three performance configurations – Light, Mid, and Max – to match customer payloads and mission objectives with minimal reconfiguration and fast flight acceptance testing.

Our MP42 modular microsatellite buses are designed for various applications, including fundamental research missions, remote sensing, and machine-to-machine communication constellations requiring high data throughput. As a mission integrator, NanoAvionics provides mission operations infrastructure, hardware, and software optimized for high-performance missions that need a large payload envelope and orbit maintenance capabilities using a high total impulse propulsion system for an extended satellite orbital lifetime.

NanoAvionics’ largest satellite built and launched is an MP42 microsatellite hosting multiple payloads and weighing over 120 kg, slightly below the MP42 platform’s maximum mass of 150 kg.

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MP42 15" Light
Base performance
MP42 15" Mid
Fast downlink
MP42 15" 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
164 W
70 kg
625 x 460 x 370 mm
150 kg
1 Mbps / 3 Mbps
4.31° (1σ)
4.40° (1σ)
15"
161 W
70 kg
625 x 460 x 370 mm
150 kg
1 Mbps / 200 Mbps
4.31° (1σ)
4.40° (1σ)
15"
157 W
70 kg
625 x 460 x 370 mm
150 kg
1 Mbps / 200 Mbps
0.04° (1σ)
0.08° (1σ)
15"
Base performance
Available Payload power (Sun tracking)
164 W
Available Payload Mass
70 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.
625 x 460 x 370 mm
Max Allowable S/C Mass
150 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
15"
Fast downlink
Available Payload power (Sun tracking)
161 W
Available Payload Mass
70 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.
625 x 460 x 370 mm
Max Allowable S/C Mass
150 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
15"
High pointing accuracy
Available Payload power (Sun tracking)
157 W
Available Payload Mass
70 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.
625 x 460 x 370 mm
Max Allowable S/C Mass
150 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
15"
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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