products supplied by nanoavionics

Overview

Products Supplied by NanoAvionics

1 Buses 3

2 Flight Computers 6

3 Communication Subsystems 8

4 Navigation Subsystems (GPS) 13

5 Attitude Determination and Control Systems 14

6 Power Systems 16

7 Structures 18

8 Propulsion Systems 19

About NanoAvionics 21

CONTENTS

Products Supplied by NanoAvionics / Overview NanoAvionics, Corp. / 2021

NanoAvionics’ flight-proven satellite buses are based on a modular and highly integral design. They deliver extended payload volume and save development costs for the customer. The bus design enables the customers to concentrate on the most important mission goals and deal with high level mission imple-mentation tasks only, such as payload development, integration and support throughout the mission.

To ensure the practical reliability of the bus, radia-tion-resistant components and design implementa-tion have been incorporated into critical systems such as the Flight Computer, Payload Controller, Electric Power System, and Communication System. The standard configuration of the nanosatellite bus is optimized for IoT, M2M, ADS-B, AIS and other commercial and emergency communication applica-tions, and scientific missions. All standard configura-tion buses are optimized to have a nominal 5 years operational lifetime in a Low Earth Orbit (LEO) environment.

01.


BusesNanoAvionics buses can be also be integrated with a propulsion system, capable of performing high impulse manoeuvres such as: orbital deployment, orbit maintenance, precision flight in formations, orbit synchronization and atmospheric drag com-pensation. This results in extended satellite orbital lifetime, uncovering new opportunities for unique customer missions and significant savings in constellation maintenance costs.

NanoAvionics also offers a single point failure redundant 12U satellite option. By doubling the critical satellite subsystems, single point failures are removed from the system, hence adding mission reliability and redundancy. Such a satellite system is designed to have a mission lifetime of 10 years in LEO.

GENERAL FEATURES

• Total Empty Bus Mass: 5,500 g / 6,500 g

• Payload Volume: up to 11U

• M12P Bus is already pre-integrated (mechanically,

electrically and functionally tested) and pre-qualified

to be ready for instant payload integration. Therefore,

final flight acceptance and flight readiness procedures

are minimized for the Customer

• Communication: S-Band / UHF / X-Band

• Inter-satellite link for regular connectivity

ADCS FEATURES

PAYLOAD POWER

• Attitude Control type: 3-axis stabilization

• Eventual Attitude determination and Control System

accuracy (including mechanical displacements of the

physical body of the satellite): up to 0.1° of pointing;

0.05° of knowledge in default configuration

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

• Attitude maneuver ability (Slew rate): Up to 5°/s

• Up to 42 W OAP, 75 W / 175 W peak, 92 Wh / 161 Wh

battery pack

PROPULSION SYSTEM NANOAVIONICS “EPSS C2”

• Thrust per Thruster: 1N BOL to 0.25N EOL

• Maximum Total Impulse (N-sec): >1700• Average Specific Impulse: 220 s

• Propellant Mass: 0.8 kg


M12P

GENERAL FEATURES

• TRL9

• Total Empty Bus Mass: 4,500 g / 5,500 g

• Payload Volume: up to 5U

• M6P Bus is already pre-integrated (mechanically, electrically

and functionally tested) and pre-qualified to be ready for

instant payload integration. Therefore, final flight acceptance

and flight readiness procedures are minimized for the

Customer

• Default operation of M6P Bus during satellite mission is

implemented at command level by execution of uploaded

scripts

• A sophisticated mission code can be prepared by the

NanoAvionics team according to separately agreed terms

and conditions

• A payload integration service can be performed by the

NanoAvionics team according to separately agreed terms

and conditions

• Inter-satellite link for regular connectivity

ADCS FEATURESPROPULSION SYSTEM NANOAVIONICS “EPSS C1.5”


• Eventual Attitude determination and Control System accu-

racy (including mechanical displacements of the physi-

cal body of the satellite): up to 0.1° of pointing; 0.05° of

knowledge in default configuration


• Attitude maneuver ability (Slew rate): Up to 5°/s

PAYLOAD POWER• Up to 29 W OAP, 75 W / 175 W peak, 92 Wh / 161 Wh battery pack

• Thrust (N) per Thruster: 1N BOL to 0.25N EOL

• Average Speci�c Impulse: 220 s• Maximum Total Impulse (N-sec): > 1000

• Propellant Mass: 0.5 kg

GENERAL FEATURES

• TRL9

• Total empty bus mass: 2500 g

• Payload volume: up to 2U

ADCS FEATURES

PAYLOAD POWER


• Eventual Attitude determination and Control System accu-

racy (including mechanical displacements of the physical

body of the satellite): up to 1.35° of pointing; 1.25° of knowl-

edge in default configuration


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

• Up to 5.5 W OAP, 25 W / 175 W peak, 23 Wh / 161 Wh

battery pack

5 Products Supplied by NanoAvionics / Overview NanoAvionics, Corp. / 2021

M3P

M6P

SatBus 3C2 is a highly integrated small satellite main bus unit containing advanced functionality:• An on-board flight computer (OBC)• An attitude determination & control system (ADCS) (optional)• Redundant UHF communication system (COMM)(optional)

SatBus 3C2 is tailored for small-sized spacecrafts and complies with the CubeSat standard. The system is designed to save customers’ time and budget, minimize required integration effort and effectively increase volume for payload as well as overall system reliability through matched hard-ware on one board. SatBus 3C2 architecture is based on an STM32 H7 series microcontroller with high-performance and low power ARM Cortex™ M7 32-bit core MCU, operating at a frequency of up to 400 MHz. The same M7-core MCU performs OBC and ADCS functions. External flash and F-RAM memories provide reliable storage for telemetry and user data. A number of various digital interfaces are available for sensor and other CubeSat hardware support.

GENERAL FEATURES

• TRL9

• UHF Digital Radios “SAT2RF1-1D“ (optional)

• CubeSat Space Protocol (CSP) support

• In-orbit firmware update

• Low power consumption

FLIGHT COMPUTER (OBC/ADCS) FEATURES

• Cortex-M7 core, clock speed up to 400 MHz (configurable)

• 1 MB of integrated RAM

• 2 MB of integrated FLASH memory

• 2×512 kB of FMC-connected FRAM memory

• 256 MB of external NOR-FLASH for data storage (2 × two

die (64 MB each) chips, QSPI)

• 2×512 kB of FRAM (SPI) for frequently changing data storage

• microSD card support (up to 32 Gb)

• On-board magnetometer and three gyroscopes

• On-board magnetorquer drivers

• Multiple CAN, SPI, I2C, UART/USART interfaces

• PWM, GPIO Outputs

• Debug interfaces: USB/SWD

02. Flight Computers

6Products Supplied by NanoAvionics / Overview NanoAvionics, Corp. / 2021

SATBUS 3C2

Payload Controller 1.5 is a subsystem dedicated to interface between the payloads and NanoAvionics M3P, M6P, M12P CubeSat bus. It has a number of different interfaces for payload connection and can buffer data from payloads. It also controls the high data through-put transmitters and transceivers to transmit the buffered data to Ground Station.

GENERAL FEATURES

• TRL9

• Cortex™ M7 core, Clock speed up to 400 MHz (configurable),

200 MHz typical

• 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


PAYLOAD CONTROLLER

GENERAL FEATURES

• TRL9

• Frequency range: 395–440 MHz

• Modulation: GFSK2

• RF Architecture: Half Duplex

• IPC – A600H class 3 assembly, soldering

per ESA specification ECSS-Q-70-08

• Receiver sensitivity (GFSK2, 2400 bps)

at 10% bit error rate: -122dBm

• RF output power: up to 3W

03. Communication Subsystems

The UHF radio utilizes a half-duplex architecture with high performance low power consumption transceiver which is controlled by a dedicated ARM Cortex-M4 MCU. The radio uses ultra-high frequency band (UHF) that is programmable in 395 to 440 MHz range. The module supports GFSK2 modulation and 2400 to 9600 bit rates. Modulation is configured to be ¼ of symbol rate and consequently, it is MSK modulation.


SATCOM UHF TRANSCEIVER

GENERAL FEATURES

GENERAL FEATURES

• TRL9

• Variable transmit bit rate from 32 kbps to 512 kbps

• Configurable Reed-Solomon and convolutional coding

forward error correction

• Output power monitoring and regulation

• CAN-bus, RS-422 and Ethernet interfaces using CubeSat

Space Protocol (CSP)

• Wide input voltage range with protection

• Integrated temperature and power monitoring

• CubeSat Kit form factor compatible aluminum enclosure

• Transmitter frequency range: 2200 to 2290 MHz

• Transmitter output power: adjustable 20 to 30 dBm, with ALC

• Receiver frequency range: 2025 to 2110 MHz

• Receiver bit rate: 32 kbps to 128 kbps

• Receiver sensitivity -106 dBm (<1% PER)

• Operating temperature: -40°C to +70°C

• Dimensions: 87 x 93 x 17 mm

• Mass: 190 g

• TRL9

• Receive frequency range: 2025-2110 MHz

• Transmit frequency range: 2200-2290 MHz

• Data rate TX: up to 10 Mbps

• Data rate RX: 128 kbps

• Transmit & Receive Modulation: BPSK, QPSK, 8PSK

(only transmit)

• Transmit power: adjustable 20-30 dB

• CAN-bus, RS-422, LVDS and Ethernet interfaces using

CubeSat Space Protocol (CSP)

• Wide input voltage range with protection

• Integrated temperature and power monitoring

• CubeSat Kit form factor compatible aluminum enclosure

• Dimensions 93.0 x 87.2 x 17.0 mm


S-BAND TRANSCEIVERS The Satlab Full-Duplex S-Band Transceiver is

designed for TM & TC on micro- and nano-satellites. The transceiver operates on the ITU space operations S-band frequencies with GMSK (BT=0.5) modulation and CCSDS recommended channel coding, enabling integration with both independent and commercial ground station networks. The unit has separate filtered RF connections for input and output, allowing for different receiving and transmitting antennas.

SRS-3.

The Satlab SRS-4 is a full-duplex S-band transceiv-er designed for high-speed data transfer on micro- and nanosatellites. The transceiver operates on the ITU space operations S-band frequencies with BPSK, QPSK and 8PSK modulation and CCSDS recommended channel coding, enabling integra-tion with both independent and commercial ground station networks. The unit has separate filtered RF connections for input and output, allowing for different receiving and transmitting antennas.

SRS-4.


GENERAL FEATURES

• TRL9• Customer’s voice message is recorded from

.mp3 or .wav file as a human voice, telegraph or any other legal sound format message

• Frequency range (configurable according

to customer requirements): uplink (RX) VHF

144-146 MHz / downlink (TX) UHF 430-440 MHz

• Operating temperature: -30 °C to +80 °C

• Operating voltage: 5 V

• Modulation: F3E (FM)

• Squelch: activation 67 Hz CTCSS tone

• Repeater Call (configurable according to

customer requirements): FM message

(Morse code or voice)

• RF downlink/uplink connectors: SMA 50 Ohm

• Receiver system: Dual conversion;

superheterodyne: 1st IF: 21.4 MHz; 2nd IF:

455 KHz

SatCOM FMTP is a high-quality FM repeater for small satellites, designed by NanoAvionics’ partner LY3H. The repeater is fully preprogrammed and configured prior to shipment according to custom-er request. No dedicated power-on signal is required, the device is either ON or OFF state and is ready for operation immediately after turn on.

SATCOM FMTP REPEATER

NanoAvionics UHF Antenna Systems consist of RF Splitter and 4 monopole antennae. RF Splitter is a key element in turnstile antenna systems that does imped-ance matching and splits one RF signal into a phasing network in order to form a single circular polarized antenna. This results in an almost omnidirectional radiation pattern with no blind spots, which can cause signal fading due to satellite tumbling. An aperture can be provided inside the splitter board for hardware integration purposes. All NanoAvionics Antenna Systems are TRL9.

• Frequency Range – 400-500 MHz

• Peak Gain – 2.86 dB

• Noise Figure (Nadir Pointing) – 360 K

• Antenna Compatibility – Turnstile/Quad-Monopole

(circular polarization)

• RF Impedance – 50 Ohm

• Max RF Power – 10 W

• Return Loss (400-500 MHz) – > 14 dB

• RF Input Connector – MCX (50 Ohm)

• Integrated Deployment System

• Temperature Range – -40 °C +85 °C

• Mass – 51 g (typical)

GENERAL FEATURES


UHF ANTENNA SYSTEMS

These specifications apply only to 1X2U configuration

GENERAL FEATURES

• TRL9• Frequency range: 2,238 – 2,288 MHz

• Gain: 6 dBi typical

• Vertical beam: ± 40°

• Horizontal beam: ± 40°

• F/B Ratio: > 20 dB

• VSWR: < 1,25 for center frequency, < 1,8 for

frequency range

• Impedance: 50 Ω• Polarization: RHCP

• Connector: SMA female (straight)

• Outer Dimensions: 70 x 70 mm

• Mass: 49 g

• Isolation RHC/LHC: 12 dB typical at 2,263 MHz

S-band Patch Antenna is designed by NanoAvionics’ partner IQ-Wireless for small satel-lite applications to implement high data rate satellite-to-ground communication. With circular polarization antenna provides a robust solution with regards to steering accuracy to the ground station and in case of a random rotation of the satellite.


S-BAND PATCH ANTENNA

• TRL9

• Stand-alone GPS receiver (L1 C/A)

• Supports PPS output

• Supports active antennas with 3.3V compatible LNA

• Integrated latch-up protection

• Integrated buffering on all inputs and outputs

• Delivered with support library and example code for use with the

receiver

• Maximum velocity: 7.8 km/s

• Position accuracy: 2.5 m CEP

• Velocity accuracy: 0.1 m/s

• Timing accuracy: 10 ns

• Typical TTFF: 30 s

• Input voltage 3.0 V - 3.5 V

• Current < 40 mA during tracking and w/o active antenna

• Size: 30 x 20 x 4 mm3

• Mass: 5 g

• Operating temperature -40 °C to + 85 °C

GENERAL FEATURES

• TRL9• Industry leading GPS antenna performance

• 15dB LNA

• Wide Input Voltage 1.8V to 5.5V

• Low Power Consumption

• Frequency 1575.42 ± 1.023MHz

• Gain: + 1.5 dBic

GENERAL FEATURES

04. Navigation Subsystems (GPS)

The Satlab GPS receiver is a small GPS receiver designed for easy integration into LEO satellites, where cost and small size are a key design driver. The receiver works fully autonomous once powered on and will start acquiring satellite data and transmitting NMEA 0183 encapsulated GPS data on the serial interface automatically.

GPS Patch Antenna is designed by NanoAvionics partner and fits all known CubeSat Structures.


GPS RECEIVER

GPS PATCH ANTENNA

GENERAL FEATURES

• TRL9• Small, light, low power

• Wide Field-Of-View

• Integrated temperature sensor

• High temperature range

• Flexible mounting (either rear or front mount)

• Flexible connector (either stack or wire)

• Delivered with calibration data

• Accuracy:

• +/- 0.5° when FOV < 45°, no albedo

• +/- 2.0° when FOV < 60°, no albedo

• Field of view: 60°

GENERAL FEATURES

• TRL9

• Suitable for CubeSat detumbling & magnetic attitude control

• Compatible with PC-104 form factor and most CubeSat structures

• 2 separate Molex PicoLock connectors for each axis torquers

• Dipole magnetic moment strength (typ.) @ 3.3 V: 0.34 Am2 (X & Y axis)

• Dipole magnetic moment strength (typ.) @ 3.3 V: 0.33 Am2 (Z axis)

• Mass: 205 g ±1%

The Digital Sun Sensor (DSS) is a compact vector sun-sensor designed by NanoAvionics team espe-cially for CubeSats with high ADCS requirements. The DSS can come with a canted unit to turn the sensor 30° and/or elevator unit.

Magnetorquers “SatBus MTQ“ are a set of two X and Y axis magnetorquer rods and one Z axis magnetorquer coil which are mounted on a PC/104 form factor PCB to enable small satellite attitude control.

05. Attitude Determination and Control Systems


SATBUS MTQ

DIGITAL SUN SENSOR

• TRL9

• Interfaces: SPI / I2C / UART / CAN

• DC Brushless Motor in a sealed housing

• Sealed Design meaning no particle emissions or contamina-

tion of peripheral devices

• IPC – A600H class 3 assembly

• Mass of RW0: 137 g, mass of 4RW0 system: 665 g (excluding

harness)

• Operational Temperature: -40 °C to +85 °C

• 4RW0 System Mechanical Design Complies with Most Cube-

sat structures

• Maximum Torque in any axis: 3.2 mNm

• Momentum storage: 20 mNms

GENERAL FEATURES

Reaction Wheels System “SatBus 4RW0“ is a set of 4 reaction/momentum wheels (RW) as integral component of redundant 3-axis control system to enable precision pointing of the nano satellite.Reaction wheels includes DC brushless motors assembled in sealed housing providing no particle emissions and preventing contamination of peripheral devices.

GENERAL FEATURES

• TRL9• APS imaging detector using CMOS process, low power consumption, high resolution • Low-noise circuit design, ensuring high sensitivity, high SNR and high accuracy • Diversity of data interface, with RS422 serial port, I2C bus and LVDS bus of star map data • Advanced and high-speed star map recognition algorithm, can achieve complete independent capture, initial capture time < 1.2 s


SATBUS 4RWO

Star trackers are devices used for measuring the line-of-sight vector to celestial objects that can be seen by the sensor. These sensors keep a map of a certain segment of the universe in memory and compare this map with the star constellation visible through the sensor FOV. If the comparison is successful, the satellite’s attitude is defined in roll, pitch and yaw. Star Tracker ST-1 is featured with the SoC system circuit and optimized design of star catalogue and star map recognition processing algorithm. As one of the smallest star sensors in the market, the Star Tracker ST-1 can achieve observation accuracy 10"(3\sigma), dynamic performance 1.5°/s, making it the most cost-effective Star Tracker at present.

STAR TRACKER ST-1

GENERAL FEATURES

• TRL9• Integrated cover glass for improved durability

and radiation protection

• Integrated by-pass diode

• NASA qualified low outgassing solar cell adhe-

sive

• Internal copper ground planes for improved

EMI compatibility

• Circuit design without current loops to avoid

spontaneous satellite spin up

• PCB thickness: < 1.7 mm

• IPC – A600H class 3 assembly, soldering per

ESA specification ECSS-Q-70-08

• Up to 30 % efficiency

• 36.85 mW/cm2 power generation capacity in

LEO (AM0)

• Operational temperature: -40 °C to +85 °C

GaAs Solar Panels are made of high-performance triple junction space grade solar cells that enable missions with high power requirements.These solar cells reach up to 30 % efficiency and have an integrated by-pass diode to protect in series connected solar cell string from shadowing effects.Solar cells are assembled using NASA qualified low outgassing adhesive materials in clean room environment. Upon request NanoAvionics offers to produce solar panels including:• Deployables• Surface mounted wire cutters• Integrated magnetometers• Attitude estimation sensors

06. Power Systems


GaAs SOLAR PANELS

• TRL9• Up to eight output converters with up to 18 output channels

• Up to six output converters can be configured to user de-

fined output voltage (3 – 18 V)

• Integrated ideal diodes

• On-board Lithium-Ion battery pack

• Integrated battery balancing

• On-board battery heaters

• Overcurrent protection, battery undervoltage and over-

voltage safety features

• External battery pack provides up to 161 Wh battery capacity

• Current, voltage and temperature logging

• Included with ready to use external battery charger

• Software configurable output channel overcurrent protection

• Implemented EPS watchdog system

• Supports CAN communication interface with CSP protocol

• EPS configuration through USB interface

• ISS Kill Switch option

• Always-ON Real Time Clock

• Up to 18 output channels (configurable voltage rail)

• 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

• High output power (up to 175 W)

GENERAL FEATURES

OUTPUTS

• Four MPPT converters (8 solar panel input channels) with

integrated ideal blocking diodes

• Solar panel voltage range: 2.6 – 18 V

• Max input power per MPPT converter: 25 W

• High charging power (up to 70 W)

INPUTS

Electrical Power Supply (EPS) System is designed to meet wide variety of customer require-ments, with high, up to 96 %, MPPT and output converter efficiency. The EPS is compatible with differ-ent size and configuration of solar panels without any additional hardware or software configurations as it is equipped with four MPPT converters with eight solar panel input channels, with wide range input voltage (2.6 – 18 V) for reliable and flexible power distribution. Each MPPT converter is integrated with Maximum Power Point Tracking capability for high, constant and efficient energy harvest. The integrated ideal diodes minimize the voltage drop to 20 mV, hence increasing the circuit efficiency and removes the need of Schottky diodes on the solar panels.


ELECTRICAL POWER SUPPLY (EPS) SYSTEM

Standard Structures (3U/6U/12U/16U) - are designed as generic, modular, compliant with the CubeSat Design Specification. The design created provides nanosatellite developers a high level of freedom in their spacecraft configuration. Avionics or payload modules are built as single 1-Unit form factor build-ing blocks that are mounted onto the primary load carrying elements.This design concept, together with the accessi-bility of the internal subsystems creates an open structure which is easy and straightforward to use, even after assembly. TRL9.

Deployment Mechanisms and Deployable Elements are miniaturized mechanisms to extend basic nanosatellite technical capabilities and maximize volume and area utilization trough:• Single deployable side panels• Double deployable side panels• Space dart (backwards swept) panels• Antenna hinges• Sensor beam hinges• Spring loaded mechanisms• Surface mounted miniature wire cutters• TRL9

Mechanisms are made of space grade materials to ensure best frictional and mechanical characteristics.

07. Structures


CUBESAT STRUCTURES

DEPLOYMENT MECHANISMS

• TRL9

• Thruster Name – EPSS C2

• Propulsion System Size – (width x depth x height) - 100 mm

x 100 mm x 200 mm

• Lead Time – 12-14 months

• Propellant Type – Ammonium Dinitramide (ADN) Blend

• Thrust (N) per Thruster – 1N BOL to 0.25N EOL

• Propulsion System Dry Mass (kg) – 1.8

• Propulsion System Wet Mass (kg) – 2.6

• Propulsion System Rad tolerance (rads) – 20k

• Propulsion System Vibration (Grms) – 14.1 qualification

• Sub – System Operating Voltage for Heaters and Valves (V) – 12

• System Telemetry Logic Voltage TLM (V) – 3.3

• Mission BOL Pressure (Bar a) - 25

• Mission EOL Pressure (Bar a) - 5.5

• Average Specific Impulse - 220 s

• Maximum Total Impulse (N-sec) - > 1700

• Performance Density (N-sec/L): 863

• Average Firing Power Consumption (W): 2 to 8

• Peak Power Consumption (W): < 21

GENERAL FEATURES

EPSS - is high performance, environmentally-friendly propulsion system for small satellite missions. The system is capable of performing constellation deploy-ment and formation flights; drag compensation and orbit maintenance; orbital maneuvering, including Hohmann transfer; synchronization and positioning of communication equipment and payload instruments; de-orbiting at the end of the mission and other functions. EPSS is fueled by an ADN-based mono-propellant (so called “green”) which has up to a 6% higher specific impulse and 24% higher energy density as compared to the hydrazine employed systems, permitting signif-icant levels of thrust to be stored within a relatively small storage volume.

08. Propulsion Systems


CHEMICAL PROPULSION SYSTEM EPSS

19

These specifications apply only to C2 configuration

• Overheat protection (Implemented in software)• Overcurrent protection (Implemented in software)• Redundant power switch• Latch-up protection • Heater shutdown function if MCU freezes

THRUSTER CATALYST HEATER

PROTECTIONS

• Normally closed type solenoids• Overheat protection (Implemented in software)• Overcurrent protection (Implemented in software)• Redundant power switch • Single event upset resistant switch circuit• Latch-up protection • Valves close if MCU freezes• Demagnetizer function

SOLENOID VALVE PROTECTIONS

• Electronic Control Unit (ECU) overheat protection (Implemented in software)• Chamber overheat protection (Implemented in software)• Propellant tank overheat protection (Implement- ed in software)• Propellant tank overpressure by overheat protection (Implemented in software)• Continuously monitors CAN interface for com- mands (such as from ADCS for abort)• Post-heat if firing stopped due to a fault (non- nominal operation)

FIRING-STATE PROTECTIONS

• Redundant temperature and pressure sensors• Redundant heaters with independent power channels• Overheat protection (Implemented in software)• Overcurrent protection (Implemented in software)• Overpressure by overheating protection (Implemented in software)• Single event upset resistant switch circuit• Latch-up protection• Heater shutdown function if MCU freezes

PROPELLANT TANK TEMPERATURE

CONTROL PROTECTIONS

Products Supplied by NanoAvionics / Overview NanoAvionics, Corp. / 2021 20


About NanoAvionics

NanoAvionics is a globally operating small satellite prime,

providing End-to-End Space Infrastructure and enabling a

wide range of satellite missions and applications through its

economically viable technology.

NanoAvionics’ consists of more than 100 driven and skillful

employees with over 85 satellite missions and commercial

projects successfully completed to date.

The company has 5 hubs globally with sophisticated

facilities in North America, Europe and the United Kingdom

to support day-to-day design, engineering, and manufac-

turing activities: ISO 7 class certified cleanroom with ISO 5

clean areas, Thermal-Vacuum chambers, modern design,

analysis and manufacturing tools, as well as assembly and

testing procedures following ESA’s and NASA‘s standards.

All of this allows to serve the needs of company's 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 clusters established with reliable

suppliers, manufacturers, test facilities and launch providers

worldwide.

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Points of Contact

NanoAvionics US, LLC-216 W Sand Bank Rd, Suite #4,Columbia, Illinois 62236, USA+1 602 284 [email protected]

NanoAvionics EU-Mokslininkų str. 2A,LT-08412 Vilnius, Lithuania+370 663 77717 [email protected]

NanoAvionics UK, Ltd-Belvedere House, Basing View,Basingstoke, Hampshire.RG21 4HG+ 44 7 [email protected]

www.nanoavionics.com

products supplied by nanoavionics

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