SPUTNIX

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About SPUTNIX

SPUTNIX (SPUTNIX LLC, ООО «СПУТНИКС») is a Russian designer and manufacturer of small-satellite hardware, founded in 2011 in Moscow as a spin-off of the Satellite Technology Division of SCANEX. The company develops and produces CubeSat platforms (OrbiCraft-Pro line in 1U/3U/6U/12U form factors), onboard subsystems (on-board computers, ADCS sensors and actuators, radio/communication modules, power systems, thermal control units), ground stations, and test equipment, and is based at the Skolkovo Technopark in Moscow.

On August 25, 2021, SITRONICS Group (a subsidiary of AFK Sistema) acquired 71.06% of SPUTNIX's shares. Sitronics Group is a large, diversified Russian technology holding whose own corporate site (sitronics.com) covers unrelated business lines (servers, EV charging, industrial IoT, satellite-data services) and does not carry a cubesat-hardware product catalog. SPUTNIX continues to operate under its own brand and product line, with its own website (sputnix.ru) hosting the full, current hardware catalog; this listing therefore uses "SPUTNIX" as the trading name and sputnix.ru as the canonical website, while noting Sitronics Group as its parent/majority shareholder.

SPUTNIX's product line has substantial flight heritage, including the TabletSat-Aurora and OrbiCraft-Pro/Zorkiy CubeSat missions, and its onboard software and ADCS algorithms have been flight-qualified across multiple missions. The company also operates or supplies ground-segment infrastructure (mission control centers, ground stations) and test facilities (anechoic chamber, air-bearing tables) supporting its satellite hardware business.

Milestones

2011 SPUTNIX founded in Moscow as a spin-off of SCANEX's Satellite Technology Division.
2021 SITRONICS Group (a subsidiary of AFK Sistema) acquires 71.06% of SPUTNIX shares.

Company Info

Headquarters Moscow, Russia, Russia

Offices 121205, Moscow, Technopark Skolkovo, Bolshoy Boulevard, 42, building 1, office 3.305 — Moscow, rus

Founded 2011 (15 years)

Specializations

manufacturer

Website sputnix.ru/en ↗

Email contact@sputnix.ru

Photos 2

Products

6U CubeSat platform with 3-axis ADCS. Up to 12 kg S/C mass, 78 Wh battery, 35 W solar panels, UHF transceiver with deployable antennas. Reaction wheels and sun orientation included.

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Parameter	Value
Form factor	6U CubeSat
Dimensions (stowed)	118.6 × 228.6 × 366 mm
Dimensions (deployed)	118.6 × 228.6 × 820 mm
Mass (w/o payload)	≤5 kg
Max S/C mass	≤12 kg
Battery capacity	78 Wh (Li-Ion 2S+2P)
Peak solar panel power	≥35 W
UHF frequency	435–438 MHz
UHF transmit power	≥30 dBm
Data rate	4800–57600 bps
ADCS pointing accuracy (sunlit)	up to 1°
ADCS pointing stability	up to 0.1°

Form factor	6U CubeSat
Dimensions (stowed)	118.6 × 228.6 × 366 mm
Max S/C mass	12 kg
Battery capacity	78 Wh
Peak solar power	35 W
ADCS pointing (sunlit)	up to 1°
UHF frequency	435–438 MHz

Minimal 6U CubeSat platform with maximum payload volume. PSS with battery, UHF transceiver, electromagnetic detumbling only — no ADCS or reaction wheels. For simple payload missions.

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Parameter	Value
Form factor	6U CubeSat
Dimensions (stowed)	118.6 × 228.6 × 366 mm
Dimensions (deployed)	118.6 × 228.6 × 820 mm
Mass (w/o payload)	≤5 kg
Max S/C mass	≤12 kg
Battery capacity	78 Wh (Li-Ion 2S+2P)
Peak solar panel power	≥35 W
UHF frequency	435–438 MHz
UHF transmit power	≥30 dBm
Data rate	4800–57600 bps

Form factor	6U CubeSat
Dimensions (stowed)	118.6 × 228.6 × 366 mm
Max S/C mass	12 kg
Battery capacity	78 Wh
Peak solar power	35 W
UHF frequency	435–438 MHz

A dual-redundant attitude control and stabilization system control unit (OSSCU, SX-SBOX-ADCU-01) running SPUTNIX's flight-qualified ADCS software.

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Dimensions, mm	101 x 100 x 20 (without fasteners)
Mass, g	220
Power voltage, V	6-36 (without galvanic isolation)
Power consumption, Wt	no more than 5 (average 2)
Duplicated interfaces	CAN2B, RS422/485
Reservation	Hot redundancy
Processor	160 MHz, ARM Cortex-M4
Storage	32 Mb ROM (Flash), 4 Mb ROM (MRAM), 16 Mb RAM
Operating system	RTOS

Hardware-in-the-loop simulation bench for developing and verifying attitude determination, stabilization and navigation systems of small spacecraft under conditions emulating LEO flight (Helmholtz/Merritt coil magnetic field, air-bearing, sun simulator, optical tracking). Available in three configurations from CubeSat (01) to educational (02) to professional small-satellite testing (03).

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Type	ADCS hardware-in-the-loop bench —
SXC config 01	CubeSat 1U/3U/6U; Helmholtz coils 2 m, Ø600 mm uniform field; air-bearing ≤ 35 kg; pointing accuracy ≤ 0.25° —
SXC config 02	Educational; Helmholtz coils 1.3 m, Ø250 mm field; air-bearing ≤ 35 kg; accuracy ≤ 1° —
SXC config 03	Professional small-sat; Merritt coils; Ø900–1300 mm field; air-bearing ≤ 160 kg; accuracy ≤ 0.3° —
Sun simulator	≥ 90,000 lx at 1.5 m, ~6000 K —
Magnetic field amplitude	± 150 µT (config 01) —
Variants	SXL-SCOE-ADCS-01 / -02 / -03 —

A frictionless air-bearing table for testing relative-motion, docking, and multi-satellite GNC algorithms.

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Overall dimensions	5000x4000x3000 mm
Active area dimensions	1860x2480 mm
Platform carrying capacity	up to 10 kg
Working clearance between table surface and platforms	up to 0.5 mm
Working body	atmospheric air
Mechanical horizon accuracy	not worse than 0.1 mm
Independent measurement system accuracy (orientation)	not worse than 1 deg
Independent measurement system accuracy (position)	not worse than 10 mm

A modular, on-site-assembled anechoic chamber (200 MHz-45 GHz) for antenna pattern and EMC testing.

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Working volume	not less than 2x2x2 m
Anechoic volume	0.7x0.7x0.7 m
Doorway dimensions	at least 1.9x1.9 m
Anechoic level	at least 20 dB (400-440 MHz range)
Shielding level	at least 40 dB (400-440 MHz range)
Pyramidal RAM height	350 mm
Mobility	yes
Radio-transparent test table	yes

A triaxial MEMS-based angular velocity sensor (SX-SBOX-AVS-MEMS-01) for small satellite attitude determination.

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Dimensions, mm	54 x 52 x 20 (without fasteners)
Mass, g	75
Power voltage, V	6-36 without galvanic isolation
Power consumption, Wt	0.6
Duplicated interfaces	CAN2B
Random component of zero signal drift at constant temperature (1σ)	2°/h
Spectral noise power density (averaging over 100 seconds, 1σ) per axis	0.15°/√h

A passive printed L1-band antenna (AFS-GNSS) for receiving GNSS positioning signals aboard a spacecraft.

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Antenna Type	Printed
Operating frequency range	1559-1607 MHz
Gain	at least 5.5 dB
Standing wave voltage coefficient	no more than 1.5
Type of polarization	Circular, RHCP
Normal ellipticity coefficient	no more than 1.7 dB
Width of radiation pattern at minus 3 dB level	at least 84 degrees
Dimensions	68 x 68 x 15 mm
Mass	61 g

A monopole UHF-band antenna converting electrical signals into electromagnetic waves for satellite communications.

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Antenna Type	monopole
Operating frequency range	400-403 MHz
Gain	at least 4 dB
Standing wave voltage coefficient	no more than 2
Type of polarization	linear
Dimensions	12.4 x 25 x 205 mm
Mass	21 g

A redundant thermal control unit (SX-SBOX-THERMU-01) that monitors and manages heaters based on analog/digital temperature sensors across the service platform and payload.

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Dimensions	200 x 130 x 30 mm
Mass	600 g
Supply voltage	22-33 V
Power consumption without heaters included, no more	5 W
Duplicated interface	CAN2B
Number of half-sets in device	2 pcs
Number of electric heaters connected per half-set	14 pcs
Power of a single heater, no more	60 W
Number of analog temperature sensors connected per half-set	36 pcs
Type of connected analog temperature sensors	P1K0.232.6W.A.010
Number of digital temperature sensors connected per half-set	14 pcs
Type of connected digital temperature sensors	DS18B20Z

GaAs solar panel with integrated electromagnetic coil for CubeSat top/bottom edges. 98×98 mm, 28% efficiency, 480–520 mA Isc, 37 g. Center aperture for sun sensors.

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Parameter	Value
Dimensions	98 × 98 × 10 mm
Mass	37 ± 3 g
Cell type	GaAs
Open circuit voltage (Voc)	5.0–5.5 V
Short circuit current (Isc)	480–520 mA
Voltage at max power (Vmp)	4.3–4.7 V
Current at max power (Imp)	440–480 mA
Efficiency	28%
Built-in coil equivalent area	1.9 m² (typ.)
Coil resistance	230–260 Ohm
Operating temperature	-30 to +50°C

Dimensions	98 × 98 × 10 mm
Mass	37 g
Cell efficiency	28%
Open circuit voltage	5.0–5.5 V
Short circuit current	480–520 mA
Built-in coil area	1.9 m²

GaAs solar panel with built-in electromagnetic coil for CubeSat side surfaces. 98×82.6 mm, 28% efficiency, 480–520 mA Isc, 30 g. Scalable for 2U and 3U frames.

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Parameter	Value
Dimensions	98 × 82.6 × 8.6 mm
Mass	30 ± 3 g
Cell type	GaAs
Open circuit voltage (Voc)	5.0–5.5 V
Short circuit current (Isc)	480–520 mA
Voltage at max power (Vmp)	4.3–4.7 V
Current at max power (Imp)	440–480 mA
Efficiency	28%
Built-in coil equivalent area	1.9 m² (typ.)
Coil resistance	230–260 Ohm
Operating temperature	-30 to +50°C

Dimensions	98 × 82.6 × 8.6 mm
Mass	30 g
Cell efficiency	28%
Open circuit voltage	5.0–5.5 V
Short circuit current	480–520 mA
Built-in coil area	1.9 m²

Raspberry Pi CM3+ carrier board with integrated ADCS controller, magnetometer, gyroscope, EM coil driver, temperature sensor, RTC, and 3-channel power switch. CAN bus throughout.

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Form factor	PC/104
Computer	Raspberry Pi CM3/CM3+
ADCS	Integrated standalone controller
Interfaces	CAN, SPI, I2C, UART, USB 2.0, Ethernet
Connectivity	WiFi hotspot/client module

Debug/development tools for OrbiCraft-Pro payloads: the SXC-MBB-03 payload base board for SXC1/SXC3 platforms (design & software released by SPUTNIX as open source), and the SXC-DEVKIT-06-BG payload developer kit for SXC6 (functional testing of platform components, the board stack and payload-compatibility work).

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Type	Payload development & debug tools —
SXC-MBB-03	Payload base board for SXC1 / SXC3 (open-source design & SW) —
SXC-DEVKIT-06-BG	Payload developer kit for SXC6 —
Use	Component & board-stack functional tests, payload compatibility —

4-flywheel reaction wheel module for 3U+ CubeSats. DC brushless motors with vacuum-rated bearings, CAN interface per driver, ±5000 RPM, max torque 8.8/8.8/4.5 mNm (X/Y/Z), 580 g.

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Parameter	Value
Dimensions	97.5 × 97.5 × 80 mm
Mass	580 ± 20 g
Supply voltage	5–12 V (up to 15 V on demand)
Idle power (4 motors at 0 RPM)	<0.8 W
Peak power (4 motors at 5000 RPM)	<12 W
Peak current per motor	up to 1.4 A
Speed range	±5000 RPM (extendable on demand)
Speed accuracy	<10 RPM
Max torque X/Y	≥8.8 mNm (extendable to 22 mNm)
Max torque Z	≥4.5 mNm (extendable to 11.2 mNm)
Full momentum X/Y	±14.5 mNms (extendable to ±33.5)
Interface	CAN2.0B 1 Mbit/s (UniCAN protocol)

Dimensions	97.5 × 97.5 × 80 mm
Mass	580 g
Supply voltage	5–12 V
Speed range	±5000 RPM
Max torque X/Y	8.8 mNm
Max torque Z	4.5 mNm
Interface	CAN2.0B 1 Mbit/s

Two-axis digital sun sensor for nanosatellites. ±60° FOV, <0.3° accuracy, 31.3×27.5×10.3 mm, 7 g, CAN interface. Factory calibrated, no customer calibration required.

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Parameter	Value
Dimensions (bus connector)	31.3 × 27.5 × 10.3 mm
Dimensions (point-to-point)	31.3 × 27.5 × 8.6 mm
Mass	7 ± 1 g
Supply voltage	5–12 V (up to 15 V)
Power consumption	30–50 mW
Interface	CAN2.0B 1 Mbit/s (UniCAN)
Field of view	±60° (cone)
Accuracy (1σ)	<0.3°
Noise	<0.01°
Telemetry rate	up to 20 Hz
Operating temperature	-30 to +50°C

Dimensions	31.3 × 27.5 × 10.3 mm
Mass	7 g
Field of view	±60°
Accuracy (1σ)	<0.3°
Noise	<0.01°
Power consumption	30–50 mW
Interface	CAN2.0B 1 Mbit/s

A high-precision fibre-optic gyroscope (FOG, SX-SBOX-AVS-FOG-01) with a control unit and 4-element sensitive assembly (3 main + 1 backup) for orientation determination.

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Dimensions of the sensor unit	275 x 275 x 160 mm (without fasteners)
Dimensions of the control unit	171 x 111 x 44 mm (without fasteners)
Power voltage, V	22-34, galvanic isolation 500V
Power consumption, Wt	up to 33
Mass of control unit with sensor unit, kg	1.7
Duplicated interfaces	CAN2B
Random component of zero signal drift at constant temperature (100 sec-averaging, 1σ) per axis	≤0.005°/h
Random component of zero signal drift when temperature changes from -40°C to +60°C (100 sec-averaging, 1σ) per axis	≤0.02°/h
Spectral density of noise power (per Allan variance) per axis	≤0.0007°/√h

A GaAs solar panel with a built-in electromagnetic coil designed for CubeSat top/bottom edges, with a central aperture for sun sensors or small payloads (SXC-SGE-03).

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Model	SPUTNIX SXC-SGE-03
Feature	Compatible with SPUTNIX SXC1 and SXC3 CubeSat frames
Feature	Diode protection circuit
Feature	Built-in planar coil
Feature	Scalable power and coils using several panels
Dimensions	98 x 98 x 10 mm (1.8mm thickness w/o connector) (±0.2mm)
Mass	37 ± 3 g
Interfaces	Hirose GT8E connectors, scalable
Cell type	GaAs
Open Circuit Voltage (Voc)	5.0...5.5 V
Short Circuit Current (Isc)	480-520 mA
Voltage at max. Power (Vmp)	4.3...4.7 V
Current at max. Power (Imp)	440-480 mA
Efficiency	28%
Coil equivalent area	1.9 m2 (typ.)
Coil resistance	230-260 Ohm
Operating temperature range	-30...+50°C
Storage temperature	-40..+60°C
Mechanical vibration	10g (request full test report)
Mechanical shock	50g (request full test report)

A GaAs solar panel with a built-in electromagnetic detumbling coil, sized for CubeSat side surfaces (SXC-SGS-03).

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Model	SPUTNIX SXC-SGS-03
Feature	Compatible with SPUTNIX SXC1 and SXC3 CubeSat frames
Feature	Diode protection circuit
Feature	Built-in planar coil
Feature	Scalable power and coils using several panels
Dimensions	98 x 82.6 x 8.6 mm (1.8mm thickness w/o connector) (±0.2mm)
Mass	30 ± 3 g
Interfaces	Hirose GT8E connectors, scalable
Cell type	GaAs
Open Circuit Voltage (Voc)	5.0...5.5 V
Short Circuit Current (Isc)	480-520 mA
Voltage at max. Power (Vmp)	4.3...4.7 V
Current at max. Power (Imp)	440-480 mA
Efficiency	28%
Coil equivalent area	1.9 m2 (typ.)
Coil resistance	230-260 Ohm
Operating temperature range	-30...+50°C
Storage temperature	-40..+60°C
Mechanical vibration	10g (request full test report)
Mechanical shock	50g (request full test report)

A power switching unit (PSU-h) distributing main/backup power lines and redundant data/timing buses between up to 8 onboard devices.

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Dimensions, mm	244 x 171 x 45 (without fasteners)
Mass, kg	1.1
Power voltage, V	22-34
Power consumption, Wt	5
Duplicated interfaces	CAN2B
Number of ports	up to 8
Reservation	cold redundancy

A power and control interface converter unit that interfaces with high-speed transmitters of target information.

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Power supply	22...33 V, galvanic isolation 500 V
Control interface	CAN, duplicated
Output power parameters	+11...+16.5 V, 30 W
Parameters of the control output interface	x4 RS-422
Dimensions	171 x 120 x 46 mm
Mass	750 g

A family of proprietary magnetic torquer rods (SX-MT-1 through SX-MT-30) used with the magnetic torquers control unit for low-accuracy attitude damping and flywheel unloading; a minimum of 3 units is installed per spacecraft.

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Model SX-MT-1	Maximum moment 1 A*m2, Consumption 0.4 Wt, Mass 200 g, Diameter 16 mm, Dimensions 140x30x30 mm
Model SX-MT-5	Maximum moment 5 A*m2, Consumption 0.6 Wt, Mass 350 g, Diameter 20 mm, Dimensions 220x50x35 mm
Model SX-MT-10	Maximum moment 10 A*m2, Consumption 0.7 Wt, Mass 550 g, Diameter 20 mm, Dimensions 320x50x35 mm
Model SX-MT-15	Maximum moment 15 A*m2, Consumption 0.8 Wt, Mass 650 g, Diameter 20 mm, Dimensions 400x50x35 mm
Model SX-MT-20	Maximum moment 20 A*m2, Consumption 1.0 Wt, Mass 800 g, Diameter 20 mm, Dimensions 470x50x35 mm
Model SX-MT-25	Maximum moment 25 A*m2, Consumption 1.2 Wt, Mass 1000 g, Diameter 22 mm, Dimensions 470x50x35 mm
Model SX-MT-30	Maximum moment 30 A*m2, Consumption 1.8 Wt, Mass 1200 g, Diameter 25 mm, Dimensions 440x50x40 mm
MT supply voltage range, V	±10, without galvanic isolation
Methods of controlling the magnetic moment	MT

A control unit (SX-SBOX-MTQU-01) driving up to three magnetic torquers via PDM channels to implement angular velocity damping and flywheel unloading.

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Dimensions, mm	54 x 48 x 20 (without fasteners)
Mass, g	85
Power voltage, V	6-36 without galvanic isolation
Power consumption, Wt	0.8
Duplicated interfaces	CAN2B
Control channels of MT	3
Method of managing channels of MT	PDM
Maximum power for each control channel of the MT, Wt	up to 2

A triaxial anisotropic-magnetoresistive magnetometer (SX-SBOX-MAG-01) used in attitude determination alongside magnetic torquers for detumbling and momentum unloading.

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Dimensions, mm	54 x 52 x 16 (without fasteners)
Mass, g	70
Power voltage, V	6-36 without galvanic isolation
Power consumption, Wt	0.8
Measurement range, nT	±100000
Measurement noise (σ), nT	100

Series of 7 magnetic torquers for microsatellite attitude control and detumbling. Dipole moments from 1 to 30 Am², masses 200–1200 g. Compatible with SPUTNIX Pallada platform.

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Model	Max moment (Am²)	Power (W)	Mass (g)	Diameter (mm)	Dimensions (mm)
SX-MT-1	1	0.4	200	16	140×30×30
SX-MT-5	5	0.6	350	20	220×50×35
SX-MT-10	10	0.7	550	20	320×50×35
SX-MT-15	15	0.8	650	20	400×50×35
SX-MT-20	20	1.0	800	20	470×50×35
SX-MT-25	25	1.2	1000	22	470×50×35
SX-MT-30	30	1.8	1200	25	440×50×40

Models available	SX-MT-1, SX-MT-5, SX-MT-10, SX-MT-15, SX-MT-20, SX-MT-25, SX-MT-30
Dipole moment range	1–30 Am²
Supply voltage	±10 V
Mass range	200–1200 g

3-axis magnetometer for microsatellite ADCS. Anisotropic magnetoresistive sensors, ±100,000 nT range, 100 nT noise, 54×52×16 mm, 70 g, CAN2B. Used for detumbling and flywheel unloading.

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Parameter	Value
Dimensions	54 × 52 × 16 mm
Mass	70 g
Supply voltage	6–36 V
Power consumption	0.8 W
Interface	CAN2B (duplicated)
Measurement range	±100,000 nT
Noise (1σ)	100 nT

Dimensions	54 × 52 × 16 mm
Mass	70 g
Measurement range	±100,000 nT
Noise (1σ)	100 nT
Power consumption	0.8 W
Interface	CAN2B (duplicated)

Control flywheel motor (CFM) for microsatellites. Max torque 0.05 Nm, max kinetic moment 2 Nms, 3.2 kg, CAN2B interface. Compatible with ECSS standards.

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Parameter	Value
Dimensions	160 × 160 × 80 mm
Mass	3.2 kg
Supply voltage	22–34 V
Peak power consumption	43 W
Nominal power consumption	10 W
Max control torque	0.05 Nm
Max kinetic moment	2 Nms
Interface	CAN2B (duplicated)

Dimensions	160 × 160 × 80 mm
Mass	3.2 kg
Supply voltage	22–34 V
Max control torque	0.05 Nm
Max kinetic moment	2 Nms
Interface	CAN2B (duplicated)

Sun sensor for microsatellites and small spacecraft. Half-angle 45° FOV, 0.15° accuracy, 43×43×16 mm, 45 g, CAN2B. Uses matrix photodetector with anti-glare algorithms.

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Parameter	Value
Dimensions	43 × 43 × 16 mm
Mass	45 g
Supply voltage	6–36 V
Power consumption	0.4 W
Interface	CAN2B (duplicated)
Field of view (half-angle)	45°
Accuracy (1σ)	0.15°

Dimensions	43 × 43 × 16 mm
Mass	45 g
Field of view (half-angle)	45°
Accuracy (1σ)	0.15°
Power consumption	0.4 W
Interface	CAN2B (duplicated)

Mission Control Center for centralized, automated control of a spacecraft or satellite constellation in Earth orbit. It aggregates data from all ground stations, then processes, analyses and stores the incoming information and issues commands.

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Type	Mission Control Center (software & facility) —
Function	Centralized automated control of spacecraft / constellations —
Inputs	Aggregates telemetry from all ground stations —
Operations	Data processing, analysis, storage and commanding —

A radiation-tolerant, dual-redundant onboard computer (SX-SBOX-OBC-01) built on a SPARC v8 Leon4FT processor with CAN, SpaceWire and optional MIL-STD-1553-like interfaces.

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Dimensions, mm	171 x 111 x 51 (without fasteners)
Mass, kg	0.86
Power voltage, V	22-34, galvanic isolation 500V
Power consumption, Wt	up to 10
Duplicated interfaces	CAN2B, SpaceWire, MKO/MIL-STD-1553-like bus (optional)

A Raspberry Pi Compute Module carrier board (SXC-MB-04-ADC) integrating an ADCS controller, gyroscope/magnetometer sensors, coil driver and power switching for CubeSats.

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Model	SPUTNIX SXC-MB-04-ADC
Feature	Flexible architecture, all devices on CAN bus interconnect
Feature	Raspberry Compute Module CM3/CM3+
Feature	Sensors on CAN bus (magnetometer, attitude rate sensor, temperature, voltages, currents)
Feature	EM torquer driver
Feature	On-board ADCS controller
Feature	Low-power board-managing MCU with autonomous detumbling mode
Feature	Bootloaders with in-flight firmware update
Configuration	Removable WiFi module
Configuration	Raspberry CM3 or CM3+ (default)
Dimensions	84 x 94 x 19 mm (±0.2mm)
Mass (w/o modules)	55 ± 3 g
Supply voltage	5..12 V
Power consumption, max	<0.25W (sensors only: ARS, magnetometer, MCU), <0.7W (ADCS controller + onboard sensors), <1.5W (sensors and RPi w/o WiFi)
Available power supply	5V output bus up to 100 mA for USB payloads
Data interfaces	CAN2.0B
Raspberry	Camera I/F, UART, I2C, SPI (2 CS), USB-HS, 10Mbit Ethernet
Debug	Raspberry removable WiFi, USB, video output
Raspberry CM3 hardware	not less than 8GB Flash (up to 32GB), 1GB SDRAM
Raspberry CM3 software	API for CAN bus, code samples, program loader
Low-power MCU	attitude rate sensor, magnetometers, EM-torquer driver, detumbling mode, bootloader
ADCS MCU	ADCS control, bootloader
Power switch	3 channels up to 600mA each
EM torquer driver	3 channels up to 500mA each
Self telemetry	power voltages/currents, coil voltages/currents, magnetometer, angular velocity, temperature
Operating temperature range	-30...+50°C (0..+50°C recommended for Raspberry)
Storage temperature	-40...+60°C
Mechanical vibration	10g (request full test report)
Mechanical shock	50g (request full test report)

The flight software (RTEMS-based) for SPUTNIX's onboard computer complex, implementing telemetry/telecommand, ADCS algorithms and device management per ECSS/CCSDS standards.

1U CubeSat satellite platform / assembly kit. The "Flight" (SXC1-GA) version is factory-assembled and tested with GaAs solar panels, ready for payload integration; an "Experimental" (SXC1) lab/educational version is also offered.

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Form factor	1U CubeSat —
Dimensions	108 × 108 × 113.5 mm
Mass (without payload)	≤ 0.95 kg (GaAs)
Max mass (with payload)	≤ 1.33 kg
Payload volume	80 × 70 × 20 mm
Solar cells	6 (GaAs / Si) —
Battery	Li-Ion 2S 5000 mAh, ≥ 39 Wh —
Bus voltage	7.4 V nominal
Radio	435–437 MHz, AX.25, up to 9600 bit/s —
ADCS	Electromagnetic, B-DOT detumbling —
Bus interface	CAN 2.0B —
Operating temperature	−30 … +60 °C
Variants	SXC1 (Experimental), SXC1-GA (Flight) —

1U CubeSat platform kit with silicon solar panels for educational and laboratory use.

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Mass	0.9-0.95 kg
Dimensions	108 x 108 x 113.5 mm
Battery capacity	39 Wh
Data bus	CAN2.0B
Solar panels	6, silicon
Radio	435-437 MHz, AX.25

Flight-ready 1U CubeSat platform with GaAs solar panels and electromagnetic ADCS.

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Mass (with payload)	1.33 kg
Solar panels	GaAs
ADCS	Electromagnetic, B-dot detumbling control

3U CubeSat satellite platform / assembly kit. The "Flight" (SXC3-GA) version is factory-assembled and tested with GaAs solar panels. Variants: Experimental (SXC3), Flight (SXC3-GA), Pro (SXC3-GA-ADC) with enhanced attitude control.

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Form factor	3U CubeSat —
Mass (without payload)	1.4 kg
Max mass (with payload)	4 kg
Dimensions	108 × 108 × 340.5 mm
Payload volume	80 × 70 × 20 mm
Solar cells	14 —
Battery	Li-Ion 2S 5000 mAh, ≥ 39 Wh —
Bus voltage	7.4 V nominal
Payload power (orbit-avg)	≥ 600 mW
Radio	435–437 MHz, AX.25 / FEC, 4800–56700 bit/s —
ADCS	B-DOT + gyro & magnetometer sensors —
Bus interface	CAN 2.0B —
Operating temperature	−30 … +60 °C
Variants	SXC3, SXC3-GA, SXC3-GA-ADC —

SPUTNIX OrbiCraft-Pro 3U assembled and factory-verified CubeSat platform with silicon solar panels, ready for payload integration and educational or experimental use.

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Form factor	3U CubeSat
On-board computer	with Raspberry Pi — 1 pc.
Power supply system	with battery unit — 1 pc.
Solar panels (side)	12 × Si solar side panels with coils
Solar panels (end edge)	2 × Si end edge solar panels with coils
Radio	UHF transceiver — 1 pc.
Antenna	UHF antenna system with service panel and RBF switch — 1 pc.
Structural elements	3U CubeSat structure, protection panels with harnessing, connection wires set
Solar panels (space missions)	GaAs (Flight modification recommended for space missions)

Flight-ready 3U CubeSat platform with GaAs solar panels across 14 panel faces.

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Mass	1.45 kg (4 kg max with payload)
Solar panels	14, GaAs

3U CubeSat platform with 3-axis ADCS, reaction wheels, and 5 sun sensors for precision pointing missions.

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ADCS	3-axis, reaction wheels + 5 sun sensors
Solar panels	GaAs

Functional 1U/3U CubeSat training kit with full set of subsystems (OBC, EPS, ADCS, comms) for universities.

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Kit type	Functional CubeSat training kit —
Form factor	1U / 3U —
Mass (1U)	~1.0 kg
Subsystems	OBC, EPS, ADCS, UHF transceiver, structure —
Ground SDR	included —
Power (orbit)	2 W
Battery	Li-Ion 10 Wh —
Use case	Universities, schools, R&D —
Software	Lua-scripted flight SW —

Microsatellite bus for spacecraft of 80–200 kg, providing service systems and accommodation for a wide range of payloads independent of the target-instrument configuration. Designed for high-resolution Earth observation and other LEO missions.

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Platform class	Microsatellite bus, 80–200 kg spacecraft —
Orbit	LEO, 500–800 km
Design lifetime	≥ 3 years
Platform mass (instruments)	≤ 120 kg
Payload mass	≤ 80 kg
Bus voltage	27 V
Solar array power (max)	up to 500 W
Average orbital power	up to 250 W
TT&C (S-band)	1 / 0.5 Mbit/s, CCSDS —
Payload downlink (X-band)	up to 1500 Mbit/s, DVB-S2 —
ADCS	3-axis; pointing ±0.05°, attitude determination ≤ 30″, stabilization ±0.001°/s —
Interfaces	SpaceWire, CAN 2.0B, LVDS —

A PC/104-compatible breadboard carrier for developing payloads and other systems that need access to the satellite's CAN bus.

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A two-module CubeSat EPS (SXC-PSS-03) consisting of a power system controller (SXC-PSU-03) and battery module (SXC-BAT-03) for solar power collection, storage, and distribution.

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A control flywheel motor (CFM, SX-SBOX-RWH-50-2.0-01) generating control torque via rotor acceleration/deceleration for larger satellite platforms.

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A 4-flywheel reaction wheel module (SXC-FW4-02) for CubeSat 3-axis attitude control, integrating drivers and control electronics on a single PC/104 card.

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The EPS regulation and control equipment (RCE) that manages battery charging/discharging and power distribution together with solar and storage batteries.

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A lightweight, 3D-metal-printed two-way spiral S-band antenna for spacecraft command/telemetry radio links.

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A full-duplex S-band command-telemetry radio link for high-speed communication with ground stations and inter-satellite links.

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A GNSS receiver unit (SX-SBOX-GNSS-01) providing precision position, velocity and time synchronization for the spacecraft.

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An assembled and manufacturer-verified 3U CubeSat engineering model (article SXC3-ADC) with silicon (Si) solar panels and triaxial ADCS, intended for adjustment of control and ADC algorithms.

An assembled and manufacturer-verified 3U CubeSat platform (article SXC3) with silicon (Si) solar panels and basic B-DOT ADCS, intended primarily as a laboratory/educational model.

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An assembled and manufacturer-verified 3U CubeSat platform (article SXC3-GA) with GaAs solar panels, ready for payload integration and suitable for actual low-Earth-orbit flight.

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An assembled and manufacturer-verified 3U CubeSat platform (article SXC3-GA-ADC-XB) with GaAs solar panels, triaxial ADCS, and an X-band transmitter with antenna, suitable for laboratory use and low-Earth-orbit flight requiring high-speed downlink.

An assembled and manufacturer-verified 3U CubeSat platform (article SXC3-GA-ADC) with GaAs solar panels and a triaxial ADCS with reaction wheels and sun sensors, suitable for laboratory use and low-Earth-orbit flight.

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A universal, combinable 12U CubeSat platform with flexible redundant subsystem configuration, high-speed X-band downlink, and gas propulsion system, designed for launch in standard production containers.

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6U CubeSat bus with 3-axis ADCS configuration and 4U payload volume.

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Minimal-configuration 6U CubeSat bus maximizing payload volume up to 5U.

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A mid-tier 6U CubeSat platform configuration of the SXC6 family with basic three-axial ADCS, allowing the spacecraft to be oriented in space via redundant subsystems.

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The simplest configuration of the SXC6 6U CubeSat platform, offering only basic service systems (power, UHF comms, electromagnetic damping) to maximize available payload volume.

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The maximum-capability 6U CubeSat platform configuration of the SXC6 family, fully equipped for remote sensing, astronomical observation, and high-speed X-band downlink.

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Full 6U CubeSat bus with star tracker, redundant systems, and X-band downlink, flight-proven on the OrbiCraft-Zorkiy Earth-observation mission.

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New-generation CubeSat platform built on SPUTNIX's extensive design, serial-production and operations heritage. Optimized structure offers maximum free payload volume and power, with improved onboard systems. Available in 4U and 16U configurations.

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A compact sun sensor (SX-SBOX-SUNS-01) for the attitude control loop, with algorithms mitigating Earth-albedo glare, suitable for microsatellites and larger platforms.

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A redundant 16-port SpaceWire routing switch with built-in MRAM storage for on-board data networking of the onboard computer complex.

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A compact, ultra-low-power two-axis digital CubeSat sun sensor (SXC-SD-01-3U) with factory calibration and CAN interface.

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Laboratory UHF transceiver for working with satellites in lab conditions over the standard radio channel. Connects to a PC via USB and is controlled by Houston CC software, allowing the frequency to be tuned in software.

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Attitude-control actuators of the SX-SBOX suite for microsatellite platforms: ADCS control unit, reaction wheel, magnetorquers and a magnetorquer control unit.

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Attitude-determination and navigation sensors of the SX-SBOX suite for microsatellite platforms: satellite navigation, GNSS antenna, MEMS and fiber-optic angular-rate sensors, magnetometer and sun sensor.

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Communications line of the SX-SBOX suite for microsatellite platforms: UHF and S-band command-and-telemetry radio links, X-band high-speed downlink (VRL-X), the high-speed-radio control unit, and UHF/S/X-band antenna-feed systems.

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Onboard computing line of the SX-SBOX instrument suite for microsatellite (Pallada-class) platforms: the onboard computer, a SpaceWire router with onboard mass memory, and flight software.

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Electrical-power line of the SX-SBOX suite for microsatellite platforms: the power regulation & control apparatus (PRU) and the power distribution/switching unit (BKP).

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Thermal-control line of the SX-SBOX suite for microsatellite platforms: the thermal-control-system control unit (BU-SOTR) and engineering services for topology optimization.

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Electrical power system (EPS) managing satellite power from the SXC-BAT-03 battery pack and up to 14 solar panels. Includes battery heating channels, Remove-Before-Flight inhibits and an economical control microcontroller.

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Sun sensor for nanosatellite attitude determination and control. The CAN interface allows a single sensor or a daisy-chain of sensors; it measures the cosine of the angle to the Sun across a wide field of view.

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GaAs (gallium arsenide) solar panels with integrated electromagnetic torquer coils for CubeSat structures. Side version (SXC-SGS-03) mounts on the side edge of a 1U body; end version (SXC-SGE-03) mounts on the end faces of 1U/3U bodies. Multiple panels can be combined.

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OrbiCraft-Pro UHF-band transceiver on a PC104 board for the spacecraft electronics stack, with an SMA antenna connector and antenna-deployment interface. Supports AX.25 and USP (FEC) protocols.

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Versatile, configurable 12U CubeSat nanosatellite platform of onboard service systems and structural elements, compatible with standard serial 12U deployers. Supports redundant onboard computers and a cold-gas propulsion option for high-accuracy remote-sensing missions.

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Versatile, configurable 6U CubeSat nanosatellite platform of onboard service systems and structural elements. Accepts third-party payloads compliant with the SXC6 ICD. Modifications: SXC6-VOL (Basic, max payload volume), SXC6-ADC (with ADCS), SXC6-RS (remote sensing).

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Anechoic chamber for testing spacecraft transceiver chains, antenna-pattern measurement, EMC testing and other purposes. Operates from 200 MHz to 45 GHz and is mobile, with a radio-transparent test table.

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Air table for testing relative motion of spacecraft: a precision aluminium horizontal surface with an even grid of holes providing near-frictionless free motion of test objects in the horizontal plane (air-cushion pucks).

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Bench for calibration and verification of small matrix and diode-type sun sensors (linear and two-dimensional). The sensor is rotated by known angles under illumination from a stationary Xe arc-lamp light source on a two-axis rotary stage.

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SPUTNIX OrbiCraft-Pro 1U CubeSat platform — assembled and factory-verified 1U nanosatellite kit with on-board computer, power system, solar panels, UHF transceiver and antenna.

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A half-duplex UHF-band transceiver providing telecommand/telemetry radio links between spacecraft and ground stations for the Pallada/SXC platform families.

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A single-board CubeSat UHF radio (SXC-UHF-02) for telemetry, telecommand and beacon transmission with in-flight reconfigurable parameters.

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"Vyunok" is an educational ground complex for receiving spacecraft radio signals, designed for experiments by schoolchildren and students. It operates within amateur-radio VHF/UHF regulations and suits contests and educational programs.

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A two-mirror Cassegrain X-band antenna for organizing high-speed radio downlinks with optional dual-polarization data transmission.

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An adaptive X-band phased-array transmitter (HDRT-X) providing high-speed downlink of payload data with in-flight adaptive data rate/modulation.

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Satellite reception and control ground station for mission control centers and education. Receives telemetry from small spacecraft in LEO and uplinks commands. The "Zavitok-M" (SXL-GND-02-M) works in VHF/UHF; the "Zavitok-S/L" (SXL-GND-02-SL) adds an S- and L-band parabolic antenna for payload-data reception.

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Model	SPUTNIX SXC-MBB-03
Feature	approved MCU with CAN bus design
Feature	user area with 2.54mm pitch
Feature	controllable power system for user area
Feature	board schematic provided
Feature	firmware source files available
Feature	bootloader available
Configuration option	firmware source files

SXC-PSU-03 Dimensions	98.4 x 96 x 19 mm (±0.2mm)
SXC-PSU-03 Mass	20 ± 2 g
Solar panels channels	3
Solar panel type	GaAs, Si
Solar panel voltage	3.5..5.5V
Maximum solar panel current per channel	1500 mA
Maximum summary solar panels current	3000 mA
System bus voltage	8V (from solar/charger), 6.0V-8.4V (from battery)
Output channels	5
Output channel maximum power	1500 mA default (up to 4000 mA)
Summary output current	5000 mA
Battery type	Li-Ion
Battery voltage	2S
Charge voltage	4.5-5.5 V
Charge current limit	<1.5A (default)
Power consumption, max (without solar power)	<0.2 W
RBF switch	Two separate RBF connectors, separate disconnectable RTC ground
Data interfaces	CAN2.0B 1Mbit/s
Data protocol	UniCAN (Sputnix)
Discrete hardware watchdog period	25h (typical)
Telemetry	Input power voltages/currents, battery voltage/current, output channel currents, temperature
Operating temperature range	-30...+50°C
Storage temperature	-40...+60°C
Mechanical vibration	10g (request full test report)
Mechanical shock	50g (request full test report)
SXC-BAT-03 Dimensions (w/o PC104 connector)	95 x 97 x 34 mm (±0.2mm, ±1mm for Z)
SXC-BAT-03 Mass	360g
SXC-BAT-03 Interfaces	PC104, RBF connector
SXC-BAT-03 Battery type	Li-Ion
SXC-BAT-03 Battery voltage	2S (5.0V-8.5V)
SXC-BAT-03 Capacity	8 Ah (not less than 32 Wh)
SXC-BAT-03 Current protection limit	5.0 A (typ.)
SXC-BAT-03 Voltage protection limits	5.0V, 8.5V
SXC-BAT-03 Telemetry	Voltage, temperature

Dimensions, mm	160 x 160 x 80 (without fasteners)
Mass, kg	3.2
Power voltage, V	22-34 (without galvanic isolation)
Peak power consumption, Wt	43
Power consumption, Wt	10
Duplicated interfaces	CAN2B
Maximum control torque, Nmax, Nm	0.05
Maximum kinetic moment, hmax, Nms	2

Model	SPUTNIX SXC-FW4-02
Feature	Complete 3-axis angular rate actuators for CubeSat satellite
Feature	Easily integrates with SPUTNIX platforms
Feature	Four brushless DC motors with vacuum-rated bearings
Feature	Wide power supply range
Feature	Momentum and current control algorithms
Feature	Voltage, current and temperature sensors for each motor
Feature	CAN interface for each separate driver
Feature	Rich telemetry and commands protocol
Feature	Bootloader with in-flight firmware update
Configuration	Increased maximum rotation speed and momentum
Configuration	CAN bus data rate
Dimensions (w/o PC104 connector)	97.5 x 97.5 x 80 mm (±1mm)
Mass	580 ± 20 g
Supply voltage	5..12V (up to 15V on demand)
Power consumption at 0 rpm	<0.8 W (all 4 motors at 0 rpm)
Power consumption at maximum	<12 W (all 4 motors at 5000 rpm)
Peak current consumption	up to 1.4 A per motor (0 to 5000 rpm)
Data interfaces	CAN2.0B 1Mbit/s
Data protocol	UniCAN (Sputnix)
Motor speed range	±5000 RPM (can be increased on demand)
Speed control accuracy	<10 RPM
Max torque (X/Y/Z projections)	not less than 8.8/8.8/4.5 mNm (can be increased to 22.0/22.0/11.2 mNm on demand)
Full torque (@5000 RPM, X/Y/Z)	±14.5/14.5/7.7 mNms (can be increased to ±33.5/33.5/19.2 mNms on demand)
Self telemetry	For each motor - rpm, torque, current, voltage
Operating environment	air, vacuum
Operating temperature range	-30...+50°C
Storage temperature	-40..+60°C
Mechanical vibration	10g (request full test report)
Mechanical shock	50g (request full test report)

Dimensions, mm	306 x 161 x 140 (without fasteners)
Mass, kg	7
Power voltage, V	22-34
Power consumption, Wt	10
Duplicated interfaces	CAN2B, RS485, SpaceWire
Redundant galvanically separated stabilized subscriber power bus	27V, ECSS-E-ST-20-20C
Redundant unstabilized subscriber power bus	27V, ECSS-E-ST-20-20C

Antenna Type	Two-way spiral
Operating frequency range	2000-2290 MHz
Gain	at least 4 dB
Standing wave voltage coefficient	no more than 1.65
Type of polarization	Circular, RHCP
Dimensions	80 x 80 x 235 mm
Mass	190 g
Width of radiation pattern at minus 3 dB level	at least 155 degrees

Dimensions, mm	117 x 111 x 48 (without fasteners and diplexer)
Mass, kg	0.85 (without diplexer)
Power voltage, V	22-34, galvanic isolation 500V
Power consumption, Wt	22 (reception + transmission), 3 (reception)
Duplicated interfaces	CAN2B, SpaceWire, RS-485, Ethernet
Operating mode	Full duplex
Operating frequency range reception, MHz	2025-2110
Operating frequency range transmission, MHz	2200-2290
Output power level, Wt	5
Symbol data transfer rate, Mbps	0.1-10
Coding	LDPC NASA C2 (7/8)
Modulation	BPSK, QPSK, 8-PSK
Protocols	CCSDS 732.1-B-1, 131.0-B-3, 232.1-B-2
Crypto protection	AES-128/256
Built-in ROM, MB	64

Mass assembled (w/o payload)	1.4 kg
Max mass allowed (w/ payload)	4 kg
Dimensions (springs pressed, antenna folded)	108x108x340.5 mm
Dimensions at rails	100x100x340.5 mm
Available volume for payload	not less than 80x70x140 mm
Output voltage	5V +-0.5 V
Output current	not more than 2A
Available average payload power on LEO	not more than 600 mW
Battery capacity	not less than 39 Wh
On-board interface	CAN2.0 B
Number of solar panels	14 pcs
Peak power per solar panel on LEO	not less than 0.9 W
Operating temperature range	-30...+60 C
Radio channel frequency	435-437 MHz, FM
Radio data rate	4800-56700 bit/s
Battery type	Li-Ion 2S 5000 mAh
ADCS algorithms	B-DOT
Sensors	Angular velocity sensor, magnetometer, temperature

Mass assembled (w/o payload)	1.45 kg
Max mass allowed (w/ payload)	4 kg
Dimensions (springs pressed, antenna folded)	108x108x340.5 mm
Dimensions at rails	100x100x340.5 mm
Available volume for payload	not less than 80x70x140 mm
Output voltage	5V +-0.5 V
Output current	not more than 2A
Available average payload power on LEO	not more than 1500 mW
Battery capacity	not less than 39 Wh
On-board interface	CAN2.0 B
Number of solar panels	14 pcs
Peak power per solar panel on LEO	not less than 2 W
Operating temperature range	-30...+60 C
Radio channel frequency	435-437 MHz, FM
Radio channel protocol	AX.25, FEC
Radio data rate	4800-56700 bit/s
Battery type	Li-Ion 2S 5000 mAh
Battery rated voltage	7.4 V
Max battery charging current	5A

Circular working orbit altitude	LEO to 600 km
Active period	not less than 1.5 years (up to 3)
Separation method	Standard container CubeSat 12U
Outer dimensions	226.3x226.3x366+-0.5 mm
Maximum mass	24 kg
Battery capacity	120 Wh
Service radio frequency	400-401 MHz
ADCS algorithms	B-DOT, sun orientation, nadir, point trace
Sensors	Star tracker, Sun sensors, GPS, Angular velocity sensor, Magnetometer
ADCS pointing accuracy	up to 0.1 deg
Propulsion system	gas PS correction
Accuracy of binding payload axis to geographic coordinates	not worse than 40 m
High frequency downlink frequency range	8-8.4 GHz
Data rate	up to 100 Mbit/s
Modulation	QPSK, 8PSK, 16APSK
Protocol	DVB-S2 - ETSI EN 302 307-1 v1.4.1

Outer dimensions transport mode	118.6x228.6x366 mm
Outer dimensions deployed	118.6x228.6x820 mm
Mass (w/o payload)	5 kg
Maximum mass	12 kg
Battery capacity	78 Wh
Peak power per solar panel	not less than 35 W
Service radio frequency	435-438 or 400-401 MHz
Data rate	2400-57600 bps
ADCS algorithms	B-DOT, sun orientation, nadir, point trace
Sensors	Sun sensors, Angular velocity sensor, Magnetometer
ADCS pointing accuracy sunlit orbit	up to 1 deg
ADCS pointing stability sunlit orbit	up to 0.1 deg
ADCS pointing accuracy eclipse orbit	up to 10 deg
Onboard interface	CAN2.0B, SPUTNIX UniCAN
Average payload power per orbit	10 W
Maximum payload power	50 W
Payload volume	4U

Outer dimensions transport mode	118.6x228.6x366 mm
Rail dimensions	100+-0.15 x 100+-0.15 x 366+-0.5 mm
Mass (w/o payload)	3.4 kg
Maximum mass	12 kg
Power supply voltage	5+-0.5 V
Power consumption	3 A
Operating temperature range	-30...+60 C
Battery type	Li-Ion 2S
Battery capacity	78 Wh
Onboard bus voltage	6.0-8.4 V (7.4 nominal)
Peak power per solar panel	not less than 15 W
Service radio frequency	435-438 or 400-401 MHz
Transmitter power	not less than 30 dBm
Receiver sensitivity	not worse than -113 dBm
Data rate	2400-57600 bps
ADCS algorithms	B-DOT
Onboard interface	CAN2.0B, SPUTNIX UniCAN
Average payload power per orbit	4.5 W
Maximum payload power	60 W
Payload volume	5U

Form factor	6U
ADCS pointing accuracy	0.1 degree
X-band downlink	DVB-S2, 10 Mbit/s
Attitude sensor	Star tracker
Redundancy	Redundant onboard systems
Flight heritage	OrbiCraft-Zorkiy Earth-observation satellite, operational since 2021

Form factor	CubeSat 4U / 16U —
Dimensions (16U)	226 × 226 × 454 mm
Bus interface	CAN 2.0B (up to 1 Mbit/s) + CAN-FD (up to 5 Mbit/s) —
TM/TC radio	Redundant, 2400–115200 bit/s, dipole + patch, 401 / 435 MHz —
Variants	SG3 4U, SG3 16U —

Dimensions, mm	43 x 43 x 16 (without fasteners)
Mass, g	45
Power voltage, V	6-36 without galvanic isolation
Power consumption, Wt	0.4
Duplicated interfaces	CAN2B
Field of view (FoV)	half-angle cone 45°
Accuracy (sigma)	0.15°

Dimensions, mm	117 x 111 x 51 (without fasteners)
Mass, kg	0.96
Power voltage, V	22-34, galvanic isolation 500V
Power consumption, Wt	4
Built-in memory, MB	8
Duplicated interfaces	CAN2B, SpaceWire
Number of ports for connection	up to 16
Exchange rate via SpaceWire, Mbps	up to 200
RMAP support	ECSS-E-ST-50-52C

Model	SPUTNIX SXC-SD-01-3U
Feature	Mid-size satellites design in light and small package
Feature	Ultra-low power CAN device
Feature	Built-in DC converter for constant consumption
Configuration	Back cover option available
Configuration	Bus-like (66100411722) and point-to-point (653104131822) connector options
Configuration	CAN bus data rate
Configuration	Telemetry frequency
Dimensions	31.3 x 27.5 x 10.3 mm (±0.2mm, with 66100411722 connector)
Dimensions	31.3 x 27.5 x 8.6 mm (±0.2mm, with 653104131822 connector)
Mass	7 ± 1 g
Supply voltage	5..12V (up to 15V on demand)
Power consumption	30-50 mW (active with CAN output)
Data interface	CAN2.0B 1Mbit/s
Data protocol	UniCAN (Sputnix)
Field of view (FOV)	±60° (cone)
Accuracy	<0.3° (1σ, any angle within FOV)
Noise	<0.01°
Telemetry frequency	up to 20 Hz
Operating temperature range	-30...+50°C
Storage temperature	-40..+60°C
Mechanical vibration	10g (request full test report)
Mechanical shock	50g (request full test report)

Type	Laboratory UHF transceiver —
Frequency range	398–410, 435–438 MHz
TX output power	10 mW (10 dBm) —
Power at antenna	28 mW
Interface	mini-USB 2.0 —
Antenna	Stick —
Mass (with antenna)	≤ 235 g
Dimensions	149 × 64 × 49 mm
Supply voltage	4.7–5.5 V
Software	Houston CC —
Operating temperature	+15 … +45 °C

ADCS control unit SX-SBOX-ADCU-01	ARM Cortex-M4 160 MHz, hot-redundant, RTOS, ≤5 W, 220 g —
Reaction wheel SX-SBOX-RWH-50-2.0-01	Max torque 0.05 N·m, momentum 2 N·m·s, 43 W peak, 3.2 kg —
Magnetorquers SX-SBOX-MTQ	SX-MT-1…SX-MT-30: dipole 1–30 A·m², 200–1200 g —
Magnetorquer control unit SX-SBOX-MTQU-01	3 channels, PWM, ≤2 W/channel, 85 g —
Interface	CAN 2.0B —

Satellite navigation SX-SBOX-GNSS-01	Position 10 m (σ), velocity 0.01 m/s, 2 W —
GNSS antenna SX-SBOX-AGG-01	1559–1607 MHz, gain ≥5.5 dB, RHCP, 61 g —
MEMS rate sensor SX-SBOX-AVS-MEMS-01	Bias drift 2°/h, noise 0.15°/√h, 0.6 W, 75 g —
Fiber-optic gyro (GIVUS) SX-SBOX-AVS-FOG-01	Bias drift ≤0.005°/h, noise ≤0.0007°/√h —
Magnetometer SX-SBOX-MAG-01	Range ±100,000 nT, noise 100 nT, 70 g —
Sun sensor SX-SBOX-SUNS-01	FOV 45° half-cone, accuracy 0.15°, 45 g —
Interface	CAN 2.0B —

SPUTNIX

About SPUTNIX

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Products

6U CubeSat Platform SXC6 ADC AS TFF

6U CubeSat Platform SXC6 ADC AS TFF

Description

Subsystems included

Specifications

6U CubeSat Platform SXC6 VOL AS TF

6U CubeSat Platform SXC6 VOL AS TF

Description

Subsystems included

Specifications

ADCS control unit

ADCS control unit

Description

Specifications

ADCS Hardware-in-the-Loop Simulation Bench

ADCS Hardware-in-the-Loop Simulation Bench

Description

Specifications

Aerotable test bench for mutual movement of spacecraft

Aerotable test bench for mutual movement of spacecraft

Description

Specifications

Anechoic chamber

Anechoic chamber

Description

Specifications

Angular velocity sensor

Angular velocity sensor

Description

Specifications

Antenna-feeder system of global navigation satellite systems

Antenna-feeder system of global navigation satellite systems

Description

Specifications

Antenna-feeder system of the UHF band

Antenna-feeder system of the UHF band

Description

Specifications

Control unit of the thermal regime support system

Control unit of the thermal regime support system

Description

Specifications

CubeSat GaAs End/Edge Solar Panel SXC-SGE-03

CubeSat GaAs End/Edge Solar Panel SXC-SGE-03

Description

Specifications

CubeSat GaAs Side Solar Panel SXC-SGS-03

CubeSat GaAs Side Solar Panel SXC-SGS-03

Description

Specifications

CubeSat OBC / ADCS Motherboard SXC-MB-04-ADC

CubeSat OBC / ADCS Motherboard SXC-MB-04-ADC

Description

Integrated subsystems

Interfaces on PC/104

Specifications

CubeSat Payload Development Tools

CubeSat Payload Development Tools

Description

Specifications

CubeSat Reaction Wheels Module SXC-FW4-02

CubeSat Reaction Wheels Module SXC-FW4-02

Description

Specifications

CubeSat Sun Sensor SXC-SD-01-3U

CubeSat Sun Sensor SXC-SD-01-3U

Description

Specifications

Fibre-Optic Gyroscope

Fibre-Optic Gyroscope

Description

Specifications

GaAs end edge solar panel with coils

GaAs end edge solar panel with coils

Description

UHF TT&C SX-SBOX-TRX-UHF-01	435–438 MHz, 5 W, up to 19200 bit/s, AX.25/USP, RX −109 dBm —
S-band TT&C SX-SBOX-TRX-S-01	RX 2025–2110 / TX 2200–2290 MHz, 5 W, up to 10 Mbit/s, LDPC, AES-128/256, CCSDS —
X-band downlink (VRL-X) SX-SBOX-XBOX	8220 MHz, 600–1750 Mbit/s, DVB-S2/S2X, ±65° scan, EIRP 68 dBm, 15 kg —
High-speed-radio control unit	CAN control, RS-422 ×4, 0.75 kg —
Antenna systems	UHF 400–403 MHz (21 g); S-band 2000–2290 MHz ≥4 dB; X-band 8000–8400 MHz ≥22.5 dB —
Interfaces	CAN 2.0B, SpaceWire, Ethernet —

Family	Onboard computing (SX-SBOX line) —
Onboard computer SX-SBOX-OBC-01	171 × 111 × 51 mm, 0.86 kg, ≤10 W; CAN2B, SpaceWire, MIL-STD-1553 (opt) —
SpaceWire router + memory SX-SBOX-SPW-OBDH-MEM-01	8 MB, up to 16 ports, SpaceWire up to 200 Mbit/s, RMAP (ECSS-E-ST-50-52C) —
Flight software	SX-SBOX-KINOSOFT —
Supply voltage	22–34 V (500 V galvanic isolation) —
Interfaces	CAN 2.0B, SpaceWire —

Regulation & control SX-SBOX-PRU-01	306 × 161 × 140 mm, 7 kg, 10 W —
Regulated isolated bus	27 V (ECSS-E-ST-20-20C) —
Unregulated bus	27 V (ECSS-E-ST-20-20C) —
Power distribution unit SX-SBOX-PDU-HI-01	244 × 171 × 45 mm, 1.1 kg, up to 8 loads, cold-redundant —
Supply voltage	22–34 V
Interfaces	CAN 2.0B, RS-485, SpaceWire —

Thermal control unit SX-SBOX-THERMU-01	200 × 130 × 30 mm, 600 g, ≤5 W (heaters off) —
Redundancy	2 half-sets —
Heater channels	14 per half-set, ≤60 W each —
Temperature sensors	36 analog (P1K0) + 14 digital (DS18B20Z) per half-set —
Topology optimization	SX-TOPOLOGY (engineering service) —
Supply voltage	22–33 V
Interface	CAN 2.0B —

Type	EPS (power conditioning unit + battery pack) —
PCU dimensions	96 × 89 × 14 mm —
Solar panel channels	3 (GaAs / Si), up to 3000 mA total —
Bus voltage	8 V (from panels) / 6.0–8.4 V (from battery) —
Output channels	4, up to 5000 mA total —
Battery type	Li-Ion / LiFePO4, 2S (5.0–8.5 V) —
Battery capacity	10.6 A·h (39.8 Wh) —
Battery heater channels	2 —
Data interface	CAN 2.0B, UART —
Telemetry	Input/output voltages & currents, battery state, temperature —
Operating temperature	−40 … +85 °C
Qualification	QT / AT (functional, vibration, shock, thermal-vacuum) —

Type	Two-axis sun sensor —
Dimensions (without connector)	28 × 23 × 7 mm —
Mass	10 g
Supply voltage	4–14 V
Power consumption	15–25 mW
Interface	CAN 2.0B —
Field of view	± 60° (FOV cone) —
Accuracy	± 0.3° (1σ), ± 0.8° (3σ) —
Noise-equivalent angle	± 0.1° —
Telemetry rate	10–20 Hz
Operating temperature	−40 … +85 °C
Qualification	QT / AT (functional, vibration, shock, thermal-vacuum) —

Cell type	GaInP/GaAs/Ge triple-junction on Ge substrate —
Cell efficiency	28 %
Dimensions	98 × 82.6 × 8.6 mm (1.7 mm thick without connector) —
Mass	30–34 g
Open-circuit voltage (Voc)	5.3 V
Short-circuit current (Isc)	500 mA
Max-power point	4.7 V / 480 mA —
Integrated torquer coil	1.9 m² equivalent area, 200 Ω —
Interface	Hirose GT8E, scalable —
Operating temperature	−40 … +85 °C
Variants	SXC-SGS-03 (side), SXC-SGE-03 (end) —
Qualification	QT / AT (functional, vibration, shock, thermal-vacuum) —

Type	UHF transceiver (PC104 board) —
Dimensions (without PC104)	87 × 93 × 13 mm —
Mass	43 g
Supply voltage	5–14 V
Power consumption	3.5 W (TX) / 0.2 W (RX) —
Operating frequency	434–438 MHz (400–401 MHz option) —
Output power	30–33 dBm (1–2 W, adjustable) —
Modulation	GMSK —
Data rate	2400–57600 bit/s
Receiver sensitivity	−119 dBm
Protocols	AX.25, USP (FEC) —
Interfaces	CAN 2.0B, UART; RF SMA 50 Ω + antenna deployment —
Operating temperature	−40 … +85 °C

Form factor	12U CubeSat —
Dimensions	226.3 × 226.3 × 366 mm
Max mass (with payload)	≤ 24 kg
Battery	Li-Ion, ≥ 120 Wh —
Bus voltage	6.0–8.4 V
Solar power (peak, LEO)	≥ 50 W
Service radio	400–401 MHz, USP+FEC, up to 57600 bit/s —
Payload downlink (X-band)	8–8.4 GHz, up to 100 Mbit/s, DVB-S2 —
ADCS	B-DOT, sun/nadir/target pointing; gyro, magnetometer, sun & star sensors —
Pointing accuracy	up to 0.1° (imaging stabilization up to 0.01°) —
Propulsion	Cold-gas correction thruster —
Operating temperature	−30 … +60 °C
Design lifetime	≥ 1.5 (up to 3) years

Form factor	6U CubeSat —
Dimensions	118.6 × 228.6 × 366 mm
Mass (without payload)	≤ 3.4 kg
Max mass (with payload)	≤ 12 kg
Battery	Li-Ion 2S, ≥ 78 Wh —
Bus voltage	6.0–8.4 V (7.4 nominal) —
Solar power (per cell, LEO)	≥ 15 W
Radio	435–438 MHz, AX.25 / USP+FEC, up to 57600 bit/s —
Transmitter / receiver	TX ≥ 30 dBm / RX −113 dBm —
Antenna	Patch, 3 dBi —
ADCS	B-DOT + gyro & magnetometer sensors —
PC interface	micro-USB, WiFi —
Bus interface	CAN 2.0B —
Operating temperature	−30 … +60 °C
Variants	SXC6-VOL, SXC6-ADC, SXC6-RS —