Microsatellite Bus MP42D - 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
MP42D small satellite bus
MP42D small satellite bus separation ring and electric propulsion system
MP42D small satellite bus
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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. Optimized for the SpaceX Falcon 9 Full Plate XL payload volume and a 31.6″ ESPA-class separation ring for orbital deployment, it can support payloads of up to 250 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. MP42D can be integrated with optional 2.5 Gbps optical intersatellite links (OISLs) for near-real-time tasking and data delivery.

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 (Base/Optional)
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 (Base/Optional)
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
480 W
250 kg
Falcon 9 Full XL Plate
500 kg
1 Mbps / 3 Mbps
4.31° (1σ)
4.40° (1σ)
24" / 31.6"
480 W
250 kg
Falcon 9 Full XL Plate
500 kg
1 Mbps / 650 Mbps
4.31° (1σ)
4.40° (1σ)
24" / 31.6"
480 W
250 kg
Falcon 9 Full XL Plate
500 kg
1 Mbps / 2.5 Gbps
0.01° (1σ) / 0.002° (1σ)
0.014° (1σ) / 0.007° (1σ)
24" / 31.6"
Base performance
Available Payload Power (Sun Tracking)
480 W
Available Payload Mass
250 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 Full XL Plate
Max Allowable S/C Mass
500 kg
Data Rates (Uplink/Downlink)
1 Mbps / 3 Mbps
Absolute Knowledge Error (Base/Optional)
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 (Base/Optional)
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" / 31.6"
Fast downlink
Available Payload Power (Sun Tracking)
480 W
Available Payload Mass
250 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 Full XL Plate
Max Allowable S/C Mass
500 kg
Data Rates (Uplink/Downlink)
1 Mbps / 650 Mbps
Absolute Knowledge Error (Base/Optional)
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 (Base/Optional)
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" / 31.6"
High pointing accuracy
Available Payload Power (Sun Tracking)
480 W
Available Payload Mass
250 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 Full XL Plate
Max Allowable S/C Mass
500 kg
Data Rates (Uplink/Downlink)
1 Mbps / 2.5 Gbps
Absolute Knowledge Error (Base/Optional)
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) / 0.002° (1σ)
Absolute Performance Error (Base/Optional)
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) / 0.007° (1σ)
Deployment Ring
24" / 31.6"
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
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