6U nanosatellite bus M6P

Download in-orbit performance data here

NanoAvionics’ flight-proven 6U satellite bus is based on a modular and highly integral design. It delivers extends payload volume and saves development costs for customers.

M6P satellite bus enables customers to concentrate on the most important mission goals and deal only with high-level mission implementation tasks, such as payload development, and its support during the mission in orbit.

The standard configuration of the nanosatellite bus is optimized for IoT, M2M, ADS-B, AIS, other commercial and emergency communication applications, and scientific missions.

M6P bus includes a propulsion system capable of performing high-impulse maneuvers such as: orbital deployment, orbit maintenance, precision flight in formations, orbit synchronization, and atmospheric drag compensation. This results in an extended satellite orbital lifetime uncovering new opportunities for unique customer missions and significant savings on constellation maintenance costs.

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6U nanosatellite bus M6P

Download in-orbit performance data here

Download M6P bus brochure here

NanoAvionics’ flight-proven 6U satellite bus is based on a modular and highly integral design. It delivers extends payload volume and saves development costs for customers.

The standard configuration of the nanosatellite bus is optimized for IoT, M2M, ADS-B, AIS, other commercial and emergency communication applications, and scientific missions.

Bus Features:
- Empty bus mass: 4500 g / 5500 g
- Max payload mass: 7500 g
- Payload volume: up to 5U
- Contains high-performance propulsion system EPSS C1K.
- M6P bus is already pre-integrated (mechanically, electrically, and functionally tested) and pre-qualified to be immediately ready for payload integration, which minimizes, final flight acceptance and flight readiness procedures for the customer.
- Sample mission code is pre-installed for the customer to be able to run system diagnostics upon delivery of the bus and quick payload integration.
- Sophisticated mission code can be prepared by the NanoAvionics team according to separately agreed terms and conditions.
- Payload integration service can be performed by the NanoAvionics team according to separately agreed terms and conditions.
Payload Controller:
- Cortex™ M7 core, Clock speed up to 400 MHz (configurable)
- 1 MB of internal RAM
- 2 MB of internal FLASH memory
- 512 kB of FMC-connected FRAM memory
- 4 MB FMC-connected SRAM
- 256 MB of external NOR-FLASH for data storage (2 x two die (64 MB each) chips, QSPI)
- 2×512 kB of FRAM (SPI) for frequently changing data storage
- Integrated TRC
- microSD NAND Memory support (up to 2 x 32 GB)
- Three On-Board PWM Controlled H-Bridges
- PWM Outputs
- FreeRTOS
- In-Orbit firmware update
- Firmware Power-on-check and Restore
- RFS – Redundant Record-based File System
- A number of Payload dedicated interfaces:
  - 100BASE-TX Ethernet port
  - CAN Interface
  - 2 x RS422 (on request interchangeable with 2 x RS485)
  - 3 x buffered SPI
  - 2 x USART/UART
  - 2 x I2C
- CSP Support
- Self-Diagnostics
- Dynamic CPU Frequency Control
- User-friendly Console
Power System:
- Input, output converter efficiency: > 96 %
- Battery cells balancing
- Configurable thermal control system
- Supported data interfaces: CAN, with CSP protocol support, UART
- Fail-safe design: in case of total microcontroller malfunction EPS will go to emergency mode and selected emergency channels will keep satellite operational
Outputs (Over-current protected):
- 4 regulated voltage rails: 3.3 V; 5 V; (3 – 18V configurable)
- Up tp 18 regulated configurable – 3.3 V / 5 V / 3 – 18 V
- Unregulated with switch: battery voltage 6.0 – 8.4 V
- Typical output channel current: 3.13 A (configurable)
- Consistent 3.3 V Output converter power: 20 W
- Consistent 5 V Output converter power: 20 W
- Consistent 3-18 V Output converter power: 20 W
- Min unregulated output power with on-board battery back (2S1P configuration): 25 W
- Min unregulated output power with external battery pack (2S7P configuration): 175 W
Inputs:
- 4 MPPT converters (8 channels) with integrated ideal blocking diodes
- Voltage: 2.6 – 18 V
- Max input power per converter: 25W
- Max charging power with on-board battery back (2S1P configuration): 10 W
- Max charging power with extended battery pack (2S7P configuration): 70 W
Batteries:
- 8 cells, 7.4 V, 13600 mAh, 92 Wh
Flight Computer (Including ADCS functionality):
- ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
- FreeRTOS
- In-orbit firmware update and Self-Diagnostics
- CSP, KISS support
- Mission planner with time scheduled script/task execution support
- Telemetry logging
ADCS sensors and actuators:
- NanoAvionics Sun Sensors
- Integrated magnetic and inertial sensors
- Reaction Wheels System NanoAvionics “SatBus 4RW0”
- Integrated NanoAvionics Magnetorquers
- Start Tracker
Attitude control type: 3-axis stabilization

Attitude pointing accuracy: up to 0.1°

Attitude pointing knowledge: up to 0.05°

Stability accuracy (Jitter): ±0.004°/s (at f>4Hz)

Attitude maneuver ability (slew rate): up to 5°/s

Operational modes:
- Sun pointing mode
- Nadir pointing mode
- Velocity pointing mode
- Ground geodetic coordinate pointing mode
- Client defined pointing mode

HIGHLIGHTED MISSIONS

Bravo and Charlie

Client name

Aurora Insight

Launch date

2021 01 24 and 2021 04 28

“Bravo” and “Charlie” are two 6U nanosatellites NanoAvionics that built, launched, and have been operating for Aurora Insight, a U.S. business analytics company for the wireless industry. Both satellites have been scanning the radio frequency (RF) environment from LEO and are a critical part of Aurora’s technology, which maps network activity around the world.

Read the press release

Tiger-2

Client name

OQ Technology

Launch date

2021 06 29

Tiger-2, a 6U nanosatellite, is the second mission for NanoAvionics with OQ Technology and the latest addition to OQ Technology’s growing low Earth orbit (LEO) constellation of nanosatellites. Their constellation intends to provide basic commercial IoT and M2M services, using 5G connectivity, to customers with a focus on Africa, Middle East, Asia, and Latin America. NanoAvionics was contracted to build, integrate and operate the nanosatellite for OQ Technology 5G IoT mission.

Read the press release

Bus Features:
- Empty bus mass: 4500 g / 5500 g
- Max payload mass: 7500 g
- Payload volume: up to 5U
- Contains high-performance propulsion system EPSS C1K.
- M6P bus is already pre-integrated (mechanically, electrically, and functionally tested) and pre-qualified to be immediately ready for payload integration, which minimizes, final flight acceptance and flight readiness procedures for the customer.
- Sample mission code is pre-installed for the customer to be able to run system diagnostics upon delivery of the bus and quick payload integration.
- Sophisticated mission code can be prepared by the NanoAvionics team according to separately agreed terms and conditions.
- Payload integration service can be performed by the NanoAvionics team according to separately agreed terms and conditions.
Payload Controller:
- Cortex™ M7 core, Clock speed up to 400 MHz (configurable)
- 1 MB of internal RAM
- 2 MB of internal FLASH memory
- 512 kB of FMC-connected FRAM memory
- 4 MB FMC-connected SRAM
- 256 MB of external NOR-FLASH for data storage (2 x two die (64 MB each) chips, QSPI)
- 2×512 kB of FRAM (SPI) for frequently changing data storage
- Integrated TRC
- microSD NAND Memory support (up to 2 x 32 GB)
- Three On-Board PWM Controlled H-Bridges
- PWM Outputs
- FreeRTOS
- In-Orbit firmware update
- Firmware Power-on-check and Restore
- RFS – Redundant Record-based File System
- A number of Payload dedicated interfaces:
  - 100BASE-TX Ethernet port
  - CAN Interface
  - 2 x RS422 (on request interchangeable with 2 x RS485)
  - 3 x buffered SPI
  - 2 x USART/UART
  - 2 x I2C
- CSP Support
- Self-Diagnostics
- Dynamic CPU Frequency Control
- User-friendly Console
Power System:
- Input, output converter efficiency: > 96 %
- Battery cells balancing
- Configurable thermal control system
- Supported data interfaces: CAN, with CSP protocol support, UART
- Fail-safe design: in case of total microcontroller malfunction EPS will go to emergency mode and selected emergency channels will keep satellite operational
Outputs (Over-current protected):
- 4 regulated voltage rails: 3.3 V; 5 V; (3 – 18V configurable)
- Up tp 18 regulated configurable – 3.3 V / 5 V / 3 – 18 V
- Unregulated with switch: battery voltage 6.0 – 8.4 V
- Typical output channel current: 3.13 A (configurable)
- Consistent 3.3 V Output converter power: 20 W
- Consistent 5 V Output converter power: 20 W
- Consistent 3-18 V Output converter power: 20 W
- Min unregulated output power with on-board battery back (2S1P configuration): 25 W
- Min unregulated output power with external battery pack (2S7P configuration): 175 W
Inputs:
- 4 MPPT converters (8 channels) with integrated ideal blocking diodes
- Voltage: 2.6 – 18 V
- Max input power per converter: 25W
- Max charging power with on-board battery back (2S1P configuration): 10 W
- Max charging power with extended battery pack (2S7P configuration): 70 W
Batteries:
- 8 cells, 7.4 V, 13600 mAh, 92 Wh
Flight Computer (Including ADCS functionality):
- ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
- FreeRTOS
- In-orbit firmware update and Self-Diagnostics
- CSP, KISS support
- Mission planner with time scheduled script/task execution support
- Telemetry logging
ADCS sensors and actuators:
- NanoAvionics Sun Sensors
- Integrated magnetic and inertial sensors
- Reaction Wheels System NanoAvionics “SatBus 4RW0”
- Integrated NanoAvionics Magnetorquers
- Start Tracker
Attitude control type: 3-axis stabilization

Attitude pointing accuracy: up to 0.1°

Attitude pointing knowledge: up to 0.05°

Stability accuracy (Jitter): ±0.004°/s (at f>4Hz)

Attitude maneuver ability (slew rate): up to 5°/s

Operational modes:
- Sun pointing mode
- Nadir pointing mode
- Velocity pointing mode
- Ground geodetic coordinate pointing mode
- Client defined pointing mode