Microsatellite Bus MP42H - NanoAvionics

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Microsatellite Bus MP42H

Microsatellite Bus MP42H

Get Access to NanoAvionics Product Catalog with Tech Specs

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 and comes with an 8″ or 15″ ESPA-class separation ring for deployment in orbit.

The versatile system is pre-installed and pre-qualified for a faster, simpler setup, allowing users to focus more time and effort on high-value tasks such as payload integration and testing. It can accommodate payloads with a total mass of 15 kg (8″) or 30kg (15″) 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 allowable 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. And these benefits are built-in – achieving such improved performance levels often requires additional non-recurring engineering (NRE) costs, so the readymade MP42H will ultimately provide significantly more capabilities for only a marginal price increase in comparison.

NanoAvionics offers three MP42H microsatellite standard performance configurations for 8″ and 15″ versions – 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 are included which 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 equally well-suited for use in single-satellite missions or as the standardized platform for an entire constellation.

The MP42H is highly versatile and is optimized for remote sensing, high data throughput and complex communications missions, emergency communications, and fundamental research missions. 

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Get Access to NanoAvionics Product Catalog with Tech Specs

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 and comes with an 8″ or 15″ ESPA-class separation ring for deployment in orbit.

The versatile system is pre-installed and pre-qualified for a faster, simpler setup, allowing users to focus more time and effort on high-value tasks such as payload integration and testing. It can accommodate payloads with a total mass of 15 kg (8″) or 30kg (15″) 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 allowable 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. And these benefits are built-in – achieving such improved performance levels often requires additional non-recurring engineering (NRE) costs, so the readymade MP42H will ultimately provide significantly more capabilities for only a marginal price increase in comparison.

NanoAvionics offers three MP42H microsatellite standard performance configurations for 8″ and 15″ versions – 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 are included which 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 equally well-suited for use in single-satellite missions or as the standardized platform for an entire constellation.

The MP42H is highly versatile and is optimized for remote sensing, high data throughput and complex communications missions, emergency communications, and fundamental research missions. 

  • MP42H 8"/15" Light Specifications
    • Bus power (Sun tracking): 87 W / 145 W
    • Available Payload mass (payload adaptor plate mass is included in the payload mass budget): 15 kg / 30 kg
    • Available Payload volume: 410(L) x 392(W) x 330(H)* mm

    *Payload height is dependent on the launch vehicle’s allowable volume and shall be confirmed with KNA in advance.

    • Max Allowable S/C mass: 50 kg / 75kg
    • Data rates and Frequencies:
      • UHF:
        • 401-402 MHz
        • Uplink/Downlink 1.6 kpbs
      • S-band:
        • Uplink 2025-2110 MHz; 53 kbps
        • Downlink 2200-2290 MHz; 3 Mbps
    • Absolute knowledge error: 4.31° (1σ)
    • Absolute performance error: 4.40° (1σ)
    • Deployment ring: 8″ or 15″
    • Battery capacity: 368 Wh / 474 Wh
    • Payload voltage channels:
      • Regulated voltage rails: 3.3, 5.0, 12.0, 28.0 V
      • Unregulated rails:
      • (Vbat, 4S): 12-16 V
      • (Vbat, 8S): 24 – 33.2 V
    • Data interfaces:
      • 1 x 100BASE-TX Ethernet
      • 1x CAN
      • 1 x RS-422 (on request RS-485)
      • 3 x SPI
      • 2 x USART/UART
      • 2 x I2C
    • Data storage: 4 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 1 mN Field Emission Electric Propulsion
  • MP42H 8"/15" Mid Specifications
    • Bus power (Sun tracking): 87 W / 145 W
    • Available Payload mass (payload adaptor plate mass is included in the payload mass budget): 15 kg / 30 kg
    • Available Payload volume: 410(L) x 392(W) x 330(H)* mm

    *Payload height is dependent on the launch vehicle’s allowable volume and shall be confirmed with KNA in advance.

    • Max Allowable S/C mass: 50 kg / 75 kg
    • Data rates and Frequencies:
      • UHF:
        • 401-402 MHz
        • Uplink/Downlink 1.6 kpbs
      • S-band:
        • Uplink 2025-2110 MHz; 53 kbps
        • Downlink 2200-2290 MHz; 3 Mbps
      • X-band:
        • Downlink 8025-8400 MHz
        • From PC Memory 80 Mbps
        • Routing from Payload up to 200 Mbps
    • Absolute knowledge error: 4.31° (1σ)
    • Absolute performance error: 4.40° (1σ)
    • Deployment ring: 8″ or 15″
    • Battery capacity: 368 Wh / 474 Wh
    • Payload voltage channels:
      • Regulated voltage rails: 3.3, 5.0, 12.0, 28.0 V
      • Unregulated rails:
      • (Vbat, 4S): 12-16 V
      • (Vbat, 8S): 24 – 33.2 V
    • Data interfaces:
      • 1 x Ethernet (8”)
      • 1 x CAN (8” / 15”)
      • 2 x UART/USART (8”)
      • 3 x SPI (8”) / 2 x SPI (15”)
      • 2 x I2C (8” / 15”)
      • 3 x IEEE 802.3 1000BASE-T (15”)
      • 3 x RS422/UART (15”)
      • Up to 20 x LVDS, GTP, GPIO (15”)
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 1 mN Field Emission Electric Propulsion
  • MP42H 8"/15" Max Specifications
    • Bus power (Sun tracking): 87 W / 145 W
    • Available Payload mass (payload adaptor plate mass is included in the payload mass budget): 15 kg / 30 kg
    • Available Payload volume: 410(L) x 392(W) x 330(H)* mm

    *Payload height is dependent on the launch vehicle’s allowable volume and shall be confirmed with KNA in advance.

    • Max Allowable S/C mass: 50 kg / 75 kg
    • Data rates and Frequencies:
      • UHF:
        • 401-402 MHz
        • Uplink/Downlink 1.6 kpbs
      • S-band:
        • Uplink 2025-2110 MHz; 53 kbps
        • Downlink 2200-2290 MHz; 3 Mbps
      • X-band:
        • Downlink 8025-8400 MHz
        • From PC Memory 80 Mbps
        • Routing from Payload up to 200 Mbps
    • Absolute knowledge error**: 0.03° (1σ)
    • Absolute performance error**: 0.08° (1σ)

    **APE and AKE values for fine determination are provided assuming Payload-AOCS sensor calibration is performed in-orbit.

    • Deployment ring: 8″ or 15″
    • Battery capacity: 368 Wh / 474 Wh
    • Payload voltage channels:
      • Regulated voltage rails: 3.3, 5.0, 12.0, 28.0 V
      • Unregulated rails:
      • (Vbat, 4S): 12-16 V
      • (Vbat, 8S): 24 – 33.2 V
    • Data interfaces:
      • 1 x Ethernet (8”)
      • 1 x CAN (8” / 15”)
      • 2 x UART/USART (8”)
      • 3 x SPI (8”) / 2 x SPI (15”)
      • 2 x I2C (8” / 15”)
      • 3 x IEEE 802.3 1000BASE-T (15”)
      • 3 x RS422/UART (15”)
      • Up to 20 x LVDS, GTP, GPIO (15”)
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 1 mN Field Emission Electric Propulsion
  • MP42H 8"/15" Light Specifications
    • Bus power (Sun tracking): 87 W / 145 W
    • Available Payload mass (payload adaptor plate mass is included in the payload mass budget): 15 kg / 30 kg
    • Available Payload volume: 410(L) x 392(W) x 330(H)* mm

    *Payload height is dependent on the launch vehicle’s allowable volume and shall be confirmed with KNA in advance.

    • Max Allowable S/C mass: 50 kg / 75kg
    • Data rates and Frequencies:
      • UHF:
        • 401-402 MHz
        • Uplink/Downlink 1.6 kpbs
      • S-band:
        • Uplink 2025-2110 MHz; 53 kbps
        • Downlink 2200-2290 MHz; 3 Mbps
    • Absolute knowledge error: 4.31° (1σ)
    • Absolute performance error: 4.40° (1σ)
    • Deployment ring: 8″ or 15″
    • Battery capacity: 368 Wh / 474 Wh
    • Payload voltage channels:
      • Regulated voltage rails: 3.3, 5.0, 12.0, 28.0 V
      • Unregulated rails:
      • (Vbat, 4S): 12-16 V
      • (Vbat, 8S): 24 – 33.2 V
    • Data interfaces:
      • 1 x 100BASE-TX Ethernet
      • 1x CAN
      • 1 x RS-422 (on request RS-485)
      • 3 x SPI
      • 2 x USART/UART
      • 2 x I2C
    • Data storage: 4 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 1 mN Field Emission Electric Propulsion
  • MP42H 8"/15" Mid Specifications
    • Bus power (Sun tracking): 87 W / 145 W
    • Available Payload mass (payload adaptor plate mass is included in the payload mass budget): 15 kg / 30 kg
    • Available Payload volume: 410(L) x 392(W) x 330(H)* mm

    *Payload height is dependent on the launch vehicle’s allowable volume and shall be confirmed with KNA in advance.

    • Max Allowable S/C mass: 50 kg / 75 kg
    • Data rates and Frequencies:
      • UHF:
        • 401-402 MHz
        • Uplink/Downlink 1.6 kpbs
      • S-band:
        • Uplink 2025-2110 MHz; 53 kbps
        • Downlink 2200-2290 MHz; 3 Mbps
      • X-band:
        • Downlink 8025-8400 MHz
        • From PC Memory 80 Mbps
        • Routing from Payload up to 200 Mbps
    • Absolute knowledge error: 4.31° (1σ)
    • Absolute performance error: 4.40° (1σ)
    • Deployment ring: 8″ or 15″
    • Battery capacity: 368 Wh / 474 Wh
    • Payload voltage channels:
      • Regulated voltage rails: 3.3, 5.0, 12.0, 28.0 V
      • Unregulated rails:
      • (Vbat, 4S): 12-16 V
      • (Vbat, 8S): 24 – 33.2 V
    • Data interfaces:
      • 1 x Ethernet (8”)
      • 1 x CAN (8” / 15”)
      • 2 x UART/USART (8”)
      • 3 x SPI (8”) / 2 x SPI (15”)
      • 2 x I2C (8” / 15”)
      • 3 x IEEE 802.3 1000BASE-T (15”)
      • 3 x RS422/UART (15”)
      • Up to 20 x LVDS, GTP, GPIO (15”)
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 1 mN Field Emission Electric Propulsion
  • MP42H 8"/15" Max Specifications
    • Bus power (Sun tracking): 87 W / 145 W
    • Available Payload mass (payload adaptor plate mass is included in the payload mass budget): 15 kg / 30 kg
    • Available Payload volume: 410(L) x 392(W) x 330(H)* mm

    *Payload height is dependent on the launch vehicle’s allowable volume and shall be confirmed with KNA in advance.

    • Max Allowable S/C mass: 50 kg / 75 kg
    • Data rates and Frequencies:
      • UHF:
        • 401-402 MHz
        • Uplink/Downlink 1.6 kpbs
      • S-band:
        • Uplink 2025-2110 MHz; 53 kbps
        • Downlink 2200-2290 MHz; 3 Mbps
      • X-band:
        • Downlink 8025-8400 MHz
        • From PC Memory 80 Mbps
        • Routing from Payload up to 200 Mbps
    • Absolute knowledge error**: 0.03° (1σ)
    • Absolute performance error**: 0.08° (1σ)

    **APE and AKE values for fine determination are provided assuming Payload-AOCS sensor calibration is performed in-orbit.

    • Deployment ring: 8″ or 15″
    • Battery capacity: 368 Wh / 474 Wh
    • Payload voltage channels:
      • Regulated voltage rails: 3.3, 5.0, 12.0, 28.0 V
      • Unregulated rails:
      • (Vbat, 4S): 12-16 V
      • (Vbat, 8S): 24 – 33.2 V
    • Data interfaces:
      • 1 x Ethernet (8”)
      • 1 x CAN (8” / 15”)
      • 2 x UART/USART (8”)
      • 3 x SPI (8”) / 2 x SPI (15”)
      • 2 x I2C (8” / 15”)
      • 3 x IEEE 802.3 1000BASE-T (15”)
      • 3 x RS422/UART (15”)
      • Up to 20 x LVDS, GTP, GPIO (15”)
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 1 mN Field Emission Electric Propulsion