3U nanosatellite bus M3P

NanoAvionics provides nanosatellite buses based on a modular and highly integral design which extends payload volume and saves development costs for customers.

Utilization of NanoAvionics’ satellite buses 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.

Minimal software and hardware customization is needed, enabling fast lead times and low satellite cost. Product architecture allows for the operation of your payload along with the entire bus using a set of simple commands provided by NanoAvionics.

Applications of the nanosatellite bus:

Educational missions
Technology in-orbit demonstration missions
Scientific missions
Commercial constellation missions and many others

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NanoAvionics provides nanosatellite buses based on a modular and highly integral design which extends payload volume and saves development costs for customers.

Applications of the nanosatellite bus:

Educational missions
Technology in-orbit demonstration missions
Scientific missions
Commercial constellation missions and many others

Bus Features:
- Empty bus mass: 1530 g
- Max payload mass: 3000 g
- Payload volume: up to 2U
- M3P bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be straight ready for the payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized 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 NanoAvionics team according to separately agreed terms and conditions.
- Payload integration service can be performed by NanoAvionics team according to separately agreed terms and conditions.
- EPSS Propulsion system as an option.
Payload Controller 1.5:
- Maximum frequency 400 MHz
- 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 × 512 kB of FRAM (SPI) for frequently changing data storage.
- MicroSD NAND Memory support (up to 2 x 32 GB).
- Three On-Board PWM Controlled H-Bridges.
- PWM Outputs.
- FreeRTOS.
- In-Orbit firmware update.
- RFS – Redundant Record-based File System.
- CSP Support.
- Self-Diagnostics.
- Dynamic CPU Frequency Control.
- User friendly Console.
- A number of Payload dedicated interfaces:
  - 100BASE-TX Ethernet port.
  - CAN Interface.
  - RS422.
  - RS485.
  - SPI.
  - USART/UART.
  - I2C.
Electrical Power System:
- Input, output converter efficiency: > 96 %
- External battery pack provides:
- - 2S2P Configuration: 46 Wh of battery capacity.
  - 2S7P Configuration: 161 Wh of battery capacity.
- 4 adjustable regulated voltage rails: 3.3V, 5V, Configurable 3V-12V.
Outputs (Over-current protected):
- 10 output channels in default, up to 18 output channels in extended output version.
- Max 3.3 V Output converter power: 20 W.
- Max 5 V Output converter power: 20 W.
- Max 3 – 12 V Output converter power: 20 W.
- Max unregulated output power with on-board battery back (2S1P configuration): 25 W.
- Max unregulated output power with external battery pack (2S7P configuration): 175 W.
Inputs:
- 4 MPPT Converters (8 channels) with Integrated Ideal Blocking Diodes.
- Solar panel input voltage: 2.6 – 15 V.
- Max input power per converter: 25 W.
- Max charging power with on-board battery back (2S1P configuration): 10 W.
- Max charging power with extended battery pack (2S7P configuration): up to 70 W.
Flight Computer (Including ADCS functionality):
- Maximum frequency 400 MHz
- 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
Attitude control type: 3-axis stabilization

Attitude pointing accuracy: up to 1.35°

Attitude pointing knowledge: up to 1.25°

Stability accuracy (Jitter): ±0.008°/s (at f>4Hz)

Attitude maneuver ability (slew rate): up to 10°/s

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

Highlighted Missions

DEWA-SAT 1

Client name

Dubai Electricity & Water Authority (DEWA)

Launch date

2022 01 13

DEWA-SAT 1 is 3U IoT nanosatellite went into low Earth orbit (LEO) onboard Transporter-3. It is part of DEWA’s (Dubai Electricity & Water Authority) Space-D programme and will support the digitalisation of Dubai’s power and water networks. Through an ambitious programme and with the expertise of NanoAvionics, DEWA intends to enhance its flexibility and agility in monitoring and managing its electrical and water networks. \

More about the mission

LS-3

Client name

Lacuna Space

Launch date

2020 09 29

LS3 is the second nanosatellite, out of three, that NanoAvionics has built, launched, and has been operating for Lacuna Space. LS3 joined the Lacuna Network, which provides a global internet-of-things (IoT) service via a nanosatellite constellation in low Earth orbit (LEO) and autonomous sensors everywhere on Earth.

Read the press release

Bus Features:
- Empty bus mass: 1530 g
- Max payload mass: 3000 g
- Payload volume: up to 2U
- M3P bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be straight ready for the payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized 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 NanoAvionics team according to separately agreed terms and conditions.
- Payload integration service can be performed by NanoAvionics team according to separately agreed terms and conditions.
- EPSS Propulsion system as an option.
Payload Controller 1.5:
- Maximum frequency 400 MHz
- 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 × 512 kB of FRAM (SPI) for frequently changing data storage.
- MicroSD NAND Memory support (up to 2 x 32 GB).
- Three On-Board PWM Controlled H-Bridges.
- PWM Outputs.
- FreeRTOS.
- In-Orbit firmware update.
- RFS – Redundant Record-based File System.
- CSP Support.
- Self-Diagnostics.
- Dynamic CPU Frequency Control.
- User friendly Console.
- A number of Payload dedicated interfaces:
  - 100BASE-TX Ethernet port.
  - CAN Interface.
  - RS422.
  - RS485.
  - SPI.
  - USART/UART.
  - I2C.
Electrical Power System:
- Input, output converter efficiency: > 96 %
- External battery pack provides:
- - 2S2P Configuration: 46 Wh of battery capacity.
  - 2S7P Configuration: 161 Wh of battery capacity.
- 4 adjustable regulated voltage rails: 3.3V, 5V, Configurable 3V-12V.
Outputs (Over-current protected):
- 10 output channels in default, up to 18 output channels in extended output version.
- Max 3.3 V Output converter power: 20 W.
- Max 5 V Output converter power: 20 W.
- Max 3 – 12 V Output converter power: 20 W.
- Max unregulated output power with on-board battery back (2S1P configuration): 25 W.
- Max unregulated output power with external battery pack (2S7P configuration): 175 W.
Inputs:
- 4 MPPT Converters (8 channels) with Integrated Ideal Blocking Diodes.
- Solar panel input voltage: 2.6 – 15 V.
- Max input power per converter: 25 W.
- Max charging power with on-board battery back (2S1P configuration): 10 W.
- Max charging power with extended battery pack (2S7P configuration): up to 70 W.
Flight Computer (Including ADCS functionality):
- Maximum frequency 400 MHz
- 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
Attitude control type: 3-axis stabilization

Attitude pointing accuracy: up to 1.35°

Attitude pointing knowledge: up to 1.25°

Stability accuracy (Jitter): ±0.008°/s (at f>4Hz)

Attitude maneuver ability (slew rate): up to 10°/s

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