Microsatellite Bus MP42D - NanoAvionics

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Microsatellite Bus MP42D

Microsatellite Bus MP42D

Get Access to NanoAvionics Product Catalog with Tech Specs

The MP42D is the largest and heaviest bus produced by NanoAvionics making it suitable for a wide range of demanding missions and services.

Microsatellites play a variety of important roles in today’s space industry, often being employed when high levels of consistency, precision, and data delivery are required. With an integrated setup and a versatile available payload footprint of 730(L)  x 730(W) x 600(H)* mm (which can be utilized in many different ways, provided the total satellite height doesn’t exceed the launch vehicle’s allowable volume) the MP42D uses a 24″ ESPA-class separation ring and has a variety of launch options.

NanoAvionics offers three standard MP42D microsatellite performance configurations – Light, Mid, and Max – providing options that best match customers’ payload, mission objectives, and budget.

This approach, combined with standardized data interfaces, control systems, and calibration requirements, ensures the MP42D can act as a robust and versatile platform to meet precise mission performance, agility, and power requirements. The system can be deployed in missions, services, and constellations for various applications including:

  • Commercial, high data throughput, and complex communications,
  • Remote sensing and advanced monitoring,
  • Emergency response and communications systems, and
  • Research and scientific projects.

The MP42D comes equipped with a propulsion system to enable the satellite to perform high-impulse maneuvers such as orbital deployment and maintenance, precision flying, orbit synchronization, and atmospheric drag compensation. Such processes can extend satellite orbital lifetime and even open up new opportunities to generate value when mission parameters change.

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Get Access to NanoAvionics Product Catalog with Tech Specs

The MP42D is the largest and heaviest bus produced by NanoAvionics making it suitable for a wide range of demanding missions and services.

Microsatellites play a variety of important roles in today’s space industry, often being employed when high levels of consistency, precision, and data delivery are required. With an integrated setup and a versatile available payload footprint of 730(L)  x 730(W) x 600(H)* mm (which can be utilized in many different ways, provided the total satellite height doesn’t exceed the launch vehicle’s allowable volume) the MP42D uses a 24″ ESPA-class separation ring and has a variety of launch options.

NanoAvionics offers three standard MP42D microsatellite performance configurations – Light, Mid, and Max – providing options that best match customers’ payload, mission objectives, and budget.

This approach, combined with standardized data interfaces, control systems, and calibration requirements, ensures the MP42D can act as a robust and versatile platform to meet precise mission performance, agility, and power requirements. The system can be deployed in missions, services, and constellations for various applications including:

  • Commercial, high data throughput, and complex communications,
  • Remote sensing and advanced monitoring,
  • Emergency response and communications systems, and
  • Research and scientific projects.

The MP42D comes equipped with a propulsion system to enable the satellite to perform high-impulse maneuvers such as orbital deployment and maintenance, precision flying, orbit synchronization, and atmospheric drag compensation. Such processes can extend satellite orbital lifetime and even open up new opportunities to generate value when mission parameters change.

  • MP42D 24" Light Specifications
    • Bus power (Sun tracking): 218 W
    • Available Payload volume: 730(L)  x 730(W) x 600(H)* mm

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

    • 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: 24″
    • Battery capacity: 852 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: 7 mN Hall Effect Thruster
  • MP42D 24" Mid Specifications
    • Bus power (Sun tracking): 218 W
    • Available Payload volume: 730(L)  x 730(W) x 600(H)* mm

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

    • 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: 24″
    • Battery capacity: 852 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:
      • 3 x IEEE 802.3 1000BASE-T
      • 1 x CAN
      • 3 x RS422/UART
      • 2 x SPI
      • 2 x I2C
      • Up to 20 x LVDS, GTP, GPIO
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 7 mN Hall Effect Thruster
  • MP42D 24" Max Specifications
    • Bus power (Sun tracking) 218 W
    • Available Payload volume: 730(L)  x 730(W) x 600(H)* mm

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

    • 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**: 0.1° (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: 24″
    • Battery capacity: 852 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:
      • 3 x IEEE 802.3 1000BASE-T
      • 1 x CAN
      • 3 x RS422/UART
      • 2 x SPI
      • 2 x I2C
      • Up to 20 x LVDS, GTP, GPIO
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 7 mN Hall Effect Thruster
  • MP42D 24" Light Specifications
    • Bus power (Sun tracking): 218 W
    • Available Payload volume: 730(L)  x 730(W) x 600(H)* mm

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

    • 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: 24″
    • Battery capacity: 852 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: 7 mN Hall Effect Thruster
  • MP42D 24" Mid Specifications
    • Bus power (Sun tracking): 218 W
    • Available Payload volume: 730(L)  x 730(W) x 600(H)* mm

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

    • 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: 24″
    • Battery capacity: 852 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:
      • 3 x IEEE 802.3 1000BASE-T
      • 1 x CAN
      • 3 x RS422/UART
      • 2 x SPI
      • 2 x I2C
      • Up to 20 x LVDS, GTP, GPIO
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 7 mN Hall Effect Thruster
  • MP42D 24" Max Specifications
    • Bus power (Sun tracking) 218 W
    • Available Payload volume: 730(L)  x 730(W) x 600(H)* mm

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

    • 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**: 0.1° (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: 24″
    • Battery capacity: 852 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:
      • 3 x IEEE 802.3 1000BASE-T
      • 1 x CAN
      • 3 x RS422/UART
      • 2 x SPI
      • 2 x I2C
      • Up to 20 x LVDS, GTP, GPIO
    • Data storage: 32 GB NAND
    • Encryption: AES-256-GCM/CBC (On-board)
    • Propulsion: 7 mN Hall Effect Thruster