Microsatellite Bus MP42 - NanoAvionics
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Meet MP42D

Our 500 kg satellite bus delivers high resilience, agility, responsive tasking, collection, and data delivery for your mission.

– 250 kg of payload mass
– 3.4 kWh of power storage
– 2.5 Gbps optical intersatellite links
– 7-year lifetime in 750 km SSO

Explore MP42D
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Small Satellite

Microsatellite Bus MP42

Small satellites offer high performance and reliability for various space applications, such as high-resolution Earth Observation, radio frequency scanning for signals intelligence (SIGINT), 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 up to 100 kg within the SpaceX Falcon 9 Half Plate payload volume. This payload volume is suitable for deployable antennas, sub-meter 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.

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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
205 W
100 kg
Falcon 9 Half Plate
200 kg
1 Mbps / 3 Mbps
4.31° (1σ)
4.40° (1σ)
15"
205 W
100 kg
Falcon 9 Half Plate
200 kg
1 Mbps / 650 Mbps
4.31° (1σ)
4.40° (1σ)
15"
205 W
100 kg
Falcon 9 Half Plate
200 kg
1 Mbps / 650 Mbps
0.01° (1σ)
0.014° (1σ)
15"
Base performance
Available Payload Power (Sun tracking)
205 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.
Falcon 9 Half Plate
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
15"
Fast downlink
Available Payload Power (Sun tracking)
205 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.
Falcon 9 Half Plate
Max Allowable S/C Mass
200 kg
Data Rates (Uplink/Downlink)
1 Mbps / 650 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)
205 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.
Falcon 9 Half Plate
Max Allowable S/C Mass
200 kg
Data Rates (Uplink/Downlink)
1 Mbps / 650 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.
0.01° (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.
0.014° (1σ)
Deployment Ring
15"
Why NanoAvionics Microsatellites/CubeSats?
  • Driving key small satellite developments for over 10 years
  • 60+ Satellites in orbit with 300+ in development
  • 7-year microsatellite lifetime in a 750 km Sun-synchronous orbit (SSO) / 5-year CubeSat lifetime in a 600 km SSO
  • 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
Configurator
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Highlighted missions
IOD.2
2025-06-23
Client Name Startical
The Startical IOD-2 satellite is a technology demonstration mission aimed at testing space-based air traffic management systems. Equipped with a payload designed to enable real-time voice communication and monitoring of aircraft from orbit, the satellite will validate key technologies for the development of a global air traffic monitoring constellation.
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HiVE
2025-01-14
Client Name constellr
constellr leverages NanoAvionics MP42 microsatellite buses for the world’s first scalable water stress monitoring system. Equipped with thermal infrared imaging payloads, the satellites monitor global land surface temperatures to provide precise data for optimizing agricultural water use, aiming to conserve up to 60 billion tons of freshwater annually.
Read more
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