M6P

High-Performance Multi-Purpose 6U Nano-Satellite Bus

www.nanoavionics.comM6P - Preconfigured Satellite Bus

Preconfigured Nano-Satellite Buses serving highly demanding commercial satellite missionsREGULAR CONNECTIVITY

MULTI-PURPOSE

POWERFUL AND RELIABLE HARDWARE

Highly integral, transparent and decentralized system allows for

fast data exchange and safe storage between the user (server)

and the satellite(s) while in orbit.

M6P is equipped with a space-proven Inter-satellite Data Relay

System (IDRS) enabling data link service via GEO satellites. This

system allows M6P to meet the highest level requirements for

data latency and acquired data-base refresh rates.

M6P is a highly versatile bus – its performance capabilities are

optimized for IoT, M2M, AIS, ADS-B applications, and supports EO

Payloads

All of the M6P subsystems have been flight-proven during

commercial, scientific and technology demonstration missions.

Latest technology developments are implemented to ensure the

practical reliability of the platform. Critical systems such as the

Flight Computer, Payload Controller, Electric Power System and

all others are 20krad radiation-tolerant and have an expected

lifetime of 10-20 years in LEO (< 1000km) in nominal conditions.

HIGH PAYLOAD DATA DOWNLINK SPEED

Up to 100 Mb/s downlink on the X-Band.

4U–5U OF PAYLOAD VOLUME

PRECONFIGURED

PROPELLED BY GREEN CHEMICAL PROPULSION SYSTEM (EPSS)

Efficient hardware layout, which utilizes the so called “tuna cans”,

allows a maximization of volume available for the payload. It also

ensures robust power properties and thermal control for sophisti-

cated and sensitive payloads, such as measurement and remote

sensing instruments. M6P is the most volume efficient nano-satellite

bus on the market.

Ready to use satellite bus for your mission. 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.

The default configuration of the M6P satellite is suitable for 80%

of missions where payload fits into 4U (2U x 2U) of volume.

Additionally, 1U of space is available for missions that do not

require a propulsion unit.

The EPSS is capable of high-impulse maneuvers including orbit

maintenance, precision flight in formations, orbit synchronization,

atmospheric drag compensation and even orbital deployment in

certain cases, resulting in an extended satellite orbital lifetime.

This translates to new opportunities for your unique missions and

significant savings on constellation maintenance costs. The

propulsion unit also provides satellites with decommissioning

utility at the end of the mission, meeting space debris mitigation

requirements of ESA and NASA.

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NanoAvionics. Engineering the Future of Commercial Space

COMPANY’S EXPERTISE

Facilities in North America, Europe and the United Kingdom.

NanoAvionics’ team of 80 driven and skillful employees have over 75 successful small satellite missions and projects under our belt, and we keep counting.

Sophisticated facilities are employed to support day-to-day design and engineering activities: ISO 7 class certified cleanroom with ISO 5 clean areas, Thermal-Vacuum chambers, modern design, analysis and manufacturing tools, assembly and testing procedures following ESA’s standards. All of this allows us to serve the needs of our most ambitious Customers.

NanoAvionics is ISO 9001 certified, following very high standard quality management procedures.

Highly streamlined production capacity under certified and controlled industrial environments.

Technological partnership cluster established with reliable suppliers, manufacturers, test facilities and launch providers worldwide.

M6P - Preconfigured Satellite Bus

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M6P Bus Specifications

General Features

Payload Controller (PC)

Payload Communication

Solar Panels (GaAs)

Power SystemNanoAvionics

“EPS”

Total empty bus mass: 4500 g / 5500 gPayload volume: up to 5UM6P bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be immediately ready for payload IntegrationSample mission code is pre-installed for the Customer to be able to run system diagnostics upon delivery of the bus, and for quick payload integration

Dual ARM® Cortex®-A7 processor running up to 1.2 GHz 2 GB DDRAM with Hardware Error Correction (ECC)Four redundant uSD cards, with > 32 GB storage capacityEthernet 1Gbit, RS422, CAN, SPI and other payload Interfaces

CAN, SPI, RS422/UART and otherMain Electrical Interfaces

Access to M6P bus telemetry over CSP networkPayload data collection and transfer via S-Band transmitter

Software Interfaces

Frequency Uplink: 2025-2110 MHzFrequency Downlink: 2200-2290 MHzBitrate (two way): up to 400 kb/s (no FEC) / up to 200 kb/s (with FEC)Output power: up to 29 dBm

Satlab S-Band Full-duplex Transceiver (default)

Satlab S-Band Full-duplex Transceiver SRS-4 (optional) Frequency Downlink: 2200-2290 MHzBitrate (two way): up to 4 Mb/sOutput power: adjustable 20-30 dB

Input, output converter efficiency: up to 96%Fail-safe design

Syrlinks EWC27 X-Band Transmitter (optional)

8 cells, 7.4 V, 13600 mAh, 92 WhBatteries:

4 regulated voltage rails: 3.3 V; 5 V; 3 V-18 V; (configurable)Up to 18 regulated configurable – 3.3 V / 5 V / 3-18 VTypical output channel current: 3.13 A (configurable)High output power (up to 175 W)

Triple junction GaInP/GaInAs/Ge epitaxial structure solar cellsECSS standard compliantHighest efficiency solar cells on the market – 30 % average efficiencyNASA-qualified low outgassing solar cell adhesive

Outputs (Over-current protected):

www.nanoavionics.comM6P - Preconfigured Satellite Bus

M6P Bus SpecificationsSubsystem

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ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHzUser-friendly consoleTelemetry loggingMission planner with time-scheduled script/task execution support

Inertial and Magnetic Sensors SystemFine Sun SensorsStar TrackerIMU

ADCS sensors:

3.2 mNm

Thrust per Thruster: 1N BOL to 0.22N EOLdelta V (available impulse): 400 NsSpecific Impulse: 213 sPropellant mass: 0.22 kg

One Reaction Wheel Maximum Torque:

20 mNmsOne Reaction Wheel Maximum Momentum Storage:

Main Satellite CAN BusBattery chargingEPS Kill Switch ResetEPS Kill Switch Override

Umbilical connector:

Reaction Wheels SystemIntegrated Magnetorquers

Detumble modeVelocity vector pointing modeNadir pointing modeSun maximum power trackingEarth target tracking according to geodetic coordinatesNadir/one axis sun-trackingUser supplied (ECI) vector tracking

UHF communication systemARM 32-bit Cortex™ M4 CPU with clock speed up to 72 MHz (configurable)External interfaces: 3xUART, CAN, GPIOFrequency range: 395-440 MHz (UHF)Modulations: GFSK2 (MSK), GFSK4 (MSK)Receiver sensitivity (GFSK2, 2400 bps) at 10% bit error rate: -127dBmRF Architecture: half duplex RF output power: up to 3W

Attitude control type: 3-axis stabilizationAttitude pointing accuracy: up to ±0.2°Attitude pointing knowledge: up to 0.05°Stability accuracy (Jitter): ± 0.008°/s (at f > 4 Hz)Attitude maneuver ability (Slew rate): Up to 10°/sOperational modes:

Actuators:

Flight Computer (Including ADCS

functionality)NanoAvionics“SatBus 3C2”

Reaction Wheels System (SatBus RW)

Propulsion SystemNanoAvionics

“EPSS C1”

Other Features

Command, Control and TelemetryNanoAvionics

“SatCOM UHF”

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M6P Bus SpecificationsSubsystem

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M6P Bus Power Configurations

M6P Software Overview

The configuration of solar panels is fully dependent on mission requirements. Therefore, for the configuration estimation the Customer shall provide NanoAvionics with inputs such as:

The NanoAvionics system runs the open source FreeRTOS real time operating system, which is “light weight”, reliable, relatively simple and easy to use. The kernel is designed specifically for integral embedded systems and provides a full set of task scheduler, resource management and synchronization features.

All configurable functions and telemetry of containing subsys-tems are accessible using CSP protocol over CAN bus during the mission and text console over UART during development. SPS API features:

Implemented software solutions allow the Customer to save integration time and reduce mission risks. Solutions are capable of maintaining the bus and are flexible to build additional functionality and features specific to the Customer’s mission.

Satellite Bus Software (SBS) covers:

Flight Computer (FC) (includes attitude control and determi-nation) subsystem;

Payload Controller (PC);

UHF Radio subsystem (COMM);

Electrical Power System (EPS);

Propulsion (Engine) Control Unit (ECU) subsystem.

Bus telemetry acquisition and storageBus configurationReal-time clockHardware diagnosticAttitude determination and controlPosition estimation from TLEMagnetic and Sun vectors estimationUHF Radio downlink/uplinkCSP Protocol supportPower distribution controlFile transferFirmware update with golden image supportSending the beacon packetsCollecting and sending real-time telemetry packetsExecuting scriptsSBS can be configured by NanoAvionics for each mission including additional functions, if requested by CustomerNanoAvionics’ integrated Command Line Interface (CLI) allows fast diagnostic out-of-the box, configuration and telemetry readout using a human-friendly text-command interface

Desired orbit parameters

Payload specifications (power and duty cycle)

Payload thermal requirements

Preliminary information on ground/orbital objects pointing (if any)

Other critical data which could have an impact on power and thermal configuration

Example power options available practically to handle thermal loads through excess heat dissipation are within the following ranges:

Note that average power available for payload highly depends on the CubeSat orbit and Customer mission requirements.

Default: No Deployable Panels Configuration giving up to

9.5 W OAP for the Payload

High Power Deployable Panel Configuration giving up to

29 W OAP for the Payload

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The M6P bus allows easy and fast integration of the payload through standardized electric, data, software, mechanical and thermal interfaces as well as extensive documentation and professional Customer support. NanoAvionics engineers can also perform the Payload integration in order to ensure smooth and reliable operations throughout the entire mission lifetime.

Additional qualification, EM compatibility or functional testing might be performed if required by the Customer or launch provider for safety or flight acceptance reasons.

The bus enables the Customer to use up to 5U for the payload, which is mechanically fastened to the structure using internal mechanical nodes. The layout of the bus allows the payload instruments to be exposed to the exterior of the satellite or to be kept covered under the share panels.

NanoAvionics has extensive documentation and excellent customer support, allowing you a smooth and quick payload integration. If you have a need to, you can request the Payload integration to be performed by NanoAvionics.

The mechanical brackets and harness needed to accommodate the payload instruments are provided by NanoAvionics to ensure mechanical rigidity and stability of the payload allocation. Thermal control, power and data interfaces are connected under the guidance or recommendations of the NanoAvionics team.

The bus package also includes all required harnesses (wires and connectors) to connect the payload and prepare the flight software through programming / debugging / umbilical interfaces which allows debugging, software upload and charging of the satellite when fully integrated.

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M6P Payload Installation

Payload Interfaces – Mechanical Layout

Serial I/O

Primary:• CAN• RS422 x 2/ UART Optional:• SPI x 3• I2C x 2• USART

• ADC x 14• PWM up to 6 • Power PWM (H-bridge)

x 3• GPIO x 16

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Launch and Logistics

NanoAvionics can provide a piggyback-launch opportunity to Low Earth Orbit (LEO). NanoAvionics’ service includes a complete launch package taking care of all aspects related to launch, logistics of the satellite, and satellite-deployer-launch vehicle integration. The complete launch package service contains:

Securing the launch opportunity on one of the suitable upcoming PSLV launches with a possibility to switch the launch time 6 months before agreed time with no additional charges;

Arrangement of launch deployer;

Technical interface control (ICD) – arrangement and coordi-nation of technical interfaces, equipment, and documenta-tion required for the launch acceptance;

Launch vehicle integration – final satellite flight preparation campaign and, if required, satellite fueling operations. Final checkout of the satellite and integration with the launch vehicle at the launch site;

Provision of the satellite orbit and attitude data at injection and commissioning support.

Logistics coordination and support – coordination of Satellite and Ground Support Equipment logistics to the launch site and facilitating travel of personnel to and from integration facilities from the airport as well as equipment re-export if needed;

Payload Interfaces – Data and Power

All signals and power channels are available on Molex Pico-Lock type connectors.

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Points of Contact

NanoAvionics HQ and US MAIT Facilities - Midland-2901 Enterprise Lane Midland,Texas 79706, USTel.: +1 432 276 3966

NanoAvionics Americas Sales and Technical Support Office - Columbia-216 W. Sand Bank Road, Columbia, Illinois 62236, USTel.: +1 602 284 7997

NanoAvionics Northern Eastern Europe & APAC Sales Office, R&D and MAIT facilities-Mokslininkų str. 2A,LT-08412 Vilnius, LithuaniaTel.: +370 663 77717

NanoAvionics Western Europe -Science & Technology Facilities CouncilRutherford Appleton LaboratoryBuilding R103 Office G10 – G13Harwell CampusOX11 0QX, United KingdomTel.: +44 741 835 1681

e-mail: info@nanoavionics.comwww.nanoavionics.com