Glavkosmos

Launch provider Russia Verified
541 Products
1 Available Slots
41 Years Active
Visit website ↗

About Glavkosmos

Glavkosmos is the commercial subsidiary of Roscosmos State Space Corporation (the Russian Federal Space Agency), headquartered in Moscow, providing international commercial services including satellite launch, payload integration, procurement of Russian space equipment, cosmonaut training, and technical space cooperation for foreign customers. Established to manage foreign commercial sales of Russian space assets and services, Glavkosmos has coordinated launch agreements on Soyuz and other Russian launch vehicles, facilitated export of Russian space components and technologies, and supported international scientific cooperation with Roscosmos. The company serves foreign governments, commercial operators, and space agencies seeking access to Russian launch vehicles, space equipment, and professional cosmonaut training programmes.

Milestones

  • 1992 Russian Federal Space Agency established
  • 2015 Reorganized as the Roscosmos State Corporation
  • Operates Soyuz crew and Progress cargo missions

Capabilities

Carries 9
1U CubeSat3U CubeSat6U CubeSat12U CubeSatSmallSat <50 kgSmallSat 50–100 kgSmallSat 100–200 kgSmallSat 200–500 kg
Target satellites
up to 24 500 kg payload mass
Launch vehicles 5
Soyuz 2.1aSoyuz 2.1bAngara A5Soyuz 2.1b/Fregat-MSoyuz 2.1b/Fregat
Delivers to 7
LEOSSOPOMEOGTOHEOLO

Photos 2

Products

541

OrbiCraft 3D is an educational kit for nanosatellite platform design. The kit is delivered in a basic configuration with a flywheel for rotation in one axis. It can be updated by the 3-axis module. It is possible to complete the orientation and stabilization tasks with the help of the lifting bar us

1 6

«Terra» space flight simulation complex is delivered on conducting experiments with satellite models such as «OrbiCraft». Together with a kit, it allows to simulate a satellite flight in the Earth’s orbit. contains: RECOMMENDATION: 1 COMPLEX FOR 1 EDUCATIONAL SITE

1 10
TRL 9 · Flight-proven

Passive 3-channel X-band output multiplexer (7330–7535 MHz, 150 W per channel, 450 W max output, ≤0.6 dB insertion loss, 15-year life).

1 13

Propellant - hydrazine. The unit consists of eight thermocatalytic low thrusters: 4 – main, and 4 – redundant. Thermal mode of the unit is ensured by 4 heaters (2 main and 2 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 4 temperature sensors. Manufacturing lead

1 3

Universal 3U CubeSat bus rated to 1500 km altitude, 3 kg dry mass, 2U/2.5 kg payload accommodation.

1 16
TRL 9 · Flight-proven

Passive 4-channel C-band output multiplexer (3430–3893 MHz, 125 W per channel, 500 W max output, ≤0.45 dB insertion loss, 15-year life).

1 14

Glavkosmos product — A Set of Stationary Control and Verification Equipment (SSCVE). Details on request.

1 9
TRL 9 · Flight-proven

Flight-proven strain-gauge absolute pressure sensor (0–11 kPa, 5% error, 0.35 kg) for liquid rocket engine control and diagnostics.

1 13

It is made according to "Regulation 98". Version: Strain gage sensor. Type of explosion protection - ”Sealed enclosure”.

1 5

It is made according to "Regulation 98". Version: inductive primary converter and amplifier, connected by an integral cable jumper L with a length of 0.15; 1.0; 1.5 m (depending on order). The type of explosion protection of the sensor is “Tight sheath”, cable jumper - “Intact cable network”.

1 5

Active suspension system for large-sized transformable spacecraft systems at ground modal testing. Simultaneously with the suspension, the dynamic parameters are estimated (velocity, acceleration, etc.) with reference to the absolute time scale.

1

Propulsive burn formation for center of mass velocity variation during spacecraft orbit control and braking.

1 11
TRL 8 · Qualified

Spacecraft propellant filling system (5000–13500 kg charge range, -40 to +40 °C, 15-year life, 24-month delivery) for aggressive liquid propellants.

1 11

Rotates through 360° along one axis (vertical), the possibility of rotation in two horizontal axises is limited. Air bearing consists of a pedestal and hemisphere-form bearing. The bearing is attached to the moving platform with small satellite or layout of satellite . Also the air bearing includes

1 3

Rotates through 360° along one axis (vertical), the possibility of rotation in two horizontal axises is limited. Air bearing consists of a pedestal and hemisphere-form bearing. The bearing is attached to the moving platform with small satellite or layout of satellite. Also the air bearing includes a

1 3

Rotates through 360° along one axis (vertical), the possibility of rotation in two horizontal axises is limited. Air bearing consists of a pedestal and hemisphere-form bearing. The bearing is attached to the moving platform with small satellite or layout of satellite. Also the air bearing includes a

1 3

Rotates through 360° along one axis (vertical), the possibility of rotation in two horizontal axises is limited. Air bearing consists of a pedestal and hemisphere-form bearing. The bearing is attached to the moving platform with small satellite or layout of satellite. Also the air bearing includes a

1 3
TRL 6 · Prototype

Compact ADCS (1 deg pointing, 0.1 deg knowledge, CAN/USB/BT interfaces) for small spacecraft, 2 W average power.

1 14

Analog transceiver circuit ORTD-LSN, together with DRT-LSN, is intended for use in the equipment of base stations and subscriber terminals of the local navigation system. Separately, VLSI ORTD-LSN can be used as the basis of the analog path in equipment for receiving and transmitting signals in the

1 9

The accelerometer provides measurement of the apparent acceleration of ballistic and space equipment.

1 3
TRL 9 · Flight-proven

All-ceramic active GNSS antenna (1571–1610 MHz, 30 dB gain, 2.0 dB noise, VSWR ≤2.0, 40 mA, 0.35 kg, 130×74×26.7 mm) for GLONASS/GPS wearable receivers.

1 16
TRL 9 · Flight-proven

Cospas-Sarsat aviation radiobeacon antenna (121.45/242.9/406 MHz, VSWR ≤1.5, 0.7 kg, -40 to +70 °C, 240×238×60 mm). Part of aircraft antenna systems.

1 16
TRL 9 · Flight-proven

Flight-proven on-board antenna array (P/L/S-band, helical/turnstile/log-periodic/whip/horn radiators) for spacecraft coverage and signal reception.

1 6
TRL 6 · Prototype

Dual-band GLONASS/GPS active microstrip antenna (1237–1614 MHz, 25 dB gain, 4 dB NF, 5 V, 90×90×30 mm, 1 kg) for navigation receivers.

1 17
TRL 6 · Prototype

Triple-band GNSS active microstrip antenna (1164–1610 MHz, GPS/GLONASS/Galileo/BeiDou, 30–32 dB gain, 3 dB NF, Ø165×40 mm, 1 kg).

1 18
TRL 9 · Flight-proven

Active geodesic GNSS antenna with rear radiation cut-off (1571–1610 MHz, 35 dB gain, 3 dB noise, VSWR ≤1.5, 1.5 kg, Ø178 mm) for surveying equipment.

1 16
TRL 9 · Flight-proven

Dual-band active geodesic GNSS antenna with rear radiation cut-off (1223–1256/1571–1610 MHz, 33/35 dB gain, 2.5 dB NF, 2.3 kg, Ø178 mm) for L1/L2 surveying.

1 18
TRL 9 · Flight-proven

All-ceramic active GNSS antenna module (1571–1610 MHz, 30 dB gain, 2.0 dB NF, VSWR ≤2.0, 30 mA, 0.15 kg, 47.5×44×19 mm) for GLONASS/GPS wearable receivers.

1 16
TRL 9 · Flight-proven

All-ceramic active GNSS antenna module (1571–1610 MHz, 30 dB gain, VSWR ≤2.0, -60 to +55 °C, 0.15 kg, 47.5×44×19 mm) for GLONASS/GPS wearable receivers.

1 16
TRL 9 · Flight-proven

Dual-band microstrip active GNSS antenna (1223–1256/1571–1610 MHz, 25 dB gain, 3.5 dB NF, 3 V, 60 mA, 0.15 kg, 60.3×60.3×18.5 mm) for L1/L2 receivers.

1 17
TRL 9 · Flight-proven

Microstrip active GNSS antenna (1571–1610 MHz, 25 dB gain, 1.7 dB NF, VSWR ≤2.0, 30 mA, 0.02 kg, 36×36×10 mm) for personal GLONASS/GPS receivers.

1 16
TRL 9 · Flight-proven

Compact microstrip active GNSS antenna (1571–1610 MHz, 25 dB gain, 1.7 dB NF, 5 V, 30 mA, 0.05 kg, 27×25×10.5 mm) for personal GLONASS/GPS receivers.

1 16
TRL 9 · Flight-proven

Dual-band microstrip active GNSS antenna (1223–1256/1571–1610 MHz, 20 dB gain, 3.5 dB NF, 3 V, 60 mA, 0.05 kg, 50×50×12 mm) for wearable L1/L2 receivers.

1 17

The transceiver single-mirror antenna system includes an antenna with a 2.4 m reflector with an irradiating system, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting devices.

1 10

The transceiver two-mirror antenna system is built on the Cassegrain system, includes an antenna with a 3.7 m reflector with an irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting devices.

1 10

The transceiver two-mirror antenna system is built on the Cassegrain system, includes an antenna with a reflector of 4.5 m with an irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting devices.

1 10

The transceiver two-mirror antenna system is built on the Cassegrain system, includes an antenna with a 2.4 m reflector with a dual-band irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting dev

1 10
TRL 9 · Flight-proven

Dual-band microstrip active GNSS antenna (1227–1257/1571–1610 MHz, 30 dB gain, 3.5 dB NF, VSWR ≤2.0, 3 V, 70 mA, 0.6 kg) for armored vehicle GPS/GLONASS receivers.

1 17

The transceiver two-mirror antenna system is built on the Cassegrain system, includes an antenna with a 6.0 m reflector with an irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting devices.

1 8
TRL 9 · Flight-proven

Mechanical antenna reflector hold-down lock (600 kg clamping force, 200 N·m bending moment, 0.35 kg, 50-actuation life).

1 10
TRL 9 · Flight-proven

Mechanical antenna reflector hold-down lock (400 kg clamping force, 200 kg side load, 0.37 kg, 50-actuation life).

1 10
TRL 9 · Flight-proven

Dual-band passive antenna for Doppler ground systems (270/2230 MHz, 3 dB gain, VSWR ≤2.0, 5 kg, 105×Ø462 mm, -40 to +50 °C). For SNS/Doppler tracking.

1 14

The receiving two-mirror antenna system is built on the Cassegrain system, it includes an antenna with a 4.1 m reflector with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. Remote polarization switching. The structure does not include radio receivers

1 9

The two-mirror receiving and transmitting antenna system is constructed according to the Cassegrain system, it includes an antenna with a 7.2 m reflector with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. The structure does not include radio receive

1 10

The receiving two-mirror antenna system is built on the Cassegrain system, it includes an antenna with a 7.2 m reflector with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. Remote polarization switching. The structure does not include radio receivers

1 9

The receiving two-mirror antenna system is built on the Cassegrain system, it includes an antenna with a 7.2 m reflector with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. Remote polarization switching. The structure does not include radio receivers

1 8

The receiving two-mirror antenna system is built on the Cassegrain system, it includes an antenna with a 7.2 m reflector with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. Remote polarization switching. The structure does not include radio receivers

1 9

The receiving two-mirror antenna system is built on the Cassegrain system, it includes an antenna with a 9.3 m reflector with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. Remote polarization switching. The structure does not include radio receivers

1 8

Dual-band active GPS/GLONASS antenna module for fixed and portable navigation receivers.

1 12
TRL 8 · Qualified

Multi-band antenna-feeder device (137/150/400 MHz, 0–64° coverage, 4 kg) for transmitting spacecraft signals and Mayak transmitter emissions.

1 11
TRL 9 · Flight-proven

Flight-proven 600 MHz telemetry antenna-feeder device (hemispheric pattern, 2.5 kg) for Meteor-M, Resource, KORONAS-FOTON spacecraft.

1 11
TRL 9 · Flight-proven

Flight-proven multi-band antenna-feeder device (400/1700/2100 MHz, 18° coverage, 25 kg) for Electro geostationary spacecraft.

1 11
TRL 9 · Flight-proven

Flight-proven 1700 MHz meteorological signal transmission antenna (0–64° coverage, 1 kg) for Meteor-M spacecraft.

1 11
TRL 9 · Flight-proven

Flight-proven GLONASS/GPS receiving antenna (1570–1618 MHz, 0–85° coverage, 0.3 kg) for Meteor-3M navigation receiver.

1 11
TRL 9 · Flight-proven

Flight-proven 137 MHz meteorological signal transmission antenna (0–64° coverage, 2 kg) for Meteor-M and Resource spacecraft.

1 11
TRL 9 · Flight-proven

Ku/Ka-band active relay AFD (13.5/15 GHz, 41 dBi gain, 55 kg, ±180°/±120° pointing) for ISS science-power module to ground station relay.

1 16
TRL 9 · Flight-proven

Flight-proven 2 GHz simultaneous Tx/Rx antenna-feeder device (85% solid angle coverage, 1 kg) for Canopus-V and RBCA spacecraft.

1 11

The transceiver two-mirror antenna system is constructed according to the Cassegrain system, it includes an antenna with a 9.3 m reflector with an irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transm

1 10

AFS are used to transmit signals in radio communication systems, broadcasting, television, as well as other radio systems using radio waves to transmit signals. The function of an antenna is to emit or receive electromagnetic waves. The electrical connection of the antenna to the source (consumer) c

1

Lens objectives for astronomic telescopes with special-dispersion glass, adaptable clear aperture and focal distance.

1 10

Monoblock equipment for regulation and monitorung of the manned spacecraft’s power supply system. It is possible to change the design of the monoblock to increase power up to 10 kW by layout of internal submodules. It is planned to operate as part of a perspective piloted transport system.

1 9

Two-phase (vapor/liquid) hermetic closed evaporating/ condensing thermal transfer system filled with a working fluid (Toluene, Ammonia, Propylene, Ethane, Methane, Nitrogen) of straight or complicated configuration.

1 5

Light-weighted aspherical mirrors made of low-CTE Sitall glass-ceramic for ground-based and space optical systems.

1 10

Asperical mirror Specific features: Item is produced in accordance with the Customer's working design documentation (WDD).

1 1

The asynchronous controlled electric motor has a 2-phase supply voltage of 40 V, 1000 Hz; the speed of rotation is not less than 16000 rpm; the minimum operating time is 150 hours.

1 3
TRL 9 · Flight-proven

Xenon-fed attitude control thruster (7.85×10⁻² N) for spacecraft attitude modes and survivability, 15.5-year mission life.

1 9

Propellant - hydrazine. The unit consists of two modified thermocatalytic low thrusters: 1 – main, and 1 – redundant. Thermal mode of the unit is ensured by 4 heaters (2 main and 2 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 4 temperature sensors. Manufacturin

1 3

Propellant - hydrazine. The unit consists of two thermocatalytic low thrusters: 1 – main, and 1 – redundant. Thermal mode of the unit is ensured by 4 heaters (2 main and 2 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 4 temperature sensors. Manufacturing lead ti

1 3

Glavkosmos product — Automated System for Launch Complex Ground Support Equipment Control. Details on request.

1 7
TRL 9 · Flight-proven

Spacecraft electrical test complex (672 discrete outputs, 1440 discrete inputs, 48 DC channels, 510 insulation channels, 450×450 cross, QNX/Windows, up to 250 m remote). Customizable.

1 18
TRL 9 · Flight-proven

Spacecraft thermal-vacuum test chamber automation (600 m³, ±150 °C, 750+ test points, 2000+ parameters, 720+ hr continuous operation).

1 11
TRL 8 · Qualified

Vision-based microsatellite ADCS verification system (0.1° attitude accuracy, 0.05 °/s angular velocity, 2+ cameras, 16+ markers) independent of the ADCS under test.

1 11
TRL 9 · Flight-proven

Flight-proven spacecraft heat pipes (450 W·m transfer, Ø6–20 mm, up to 6 m, -133 to +227 °C) with 100+ satellite heritage. Customizable.

1 15

Passed a full cycle of testing according to the European standard PSS49 and flight applications from European, Chinese and American partners. The arterial design of the capillary structure allows you to increase the power of heat pipes without increasing their mass characteristics, to increase their

1
TRL 5 · Development

Compact sealed fiber-optic gyro IMU (3-axis angular rate) being developed for future manned spacecraft, 10-year service life.

1 7
TRL 5 · Development

Space bio-crystallizer for ISS protein crystal growth experiments (liquid/counter and gas diffusion methods, zero-gravity). Created for Bion-M mission. Customizable.

1 7
TRL 9 · Flight-proven

Flight-proven UDMH/NTO bipropellant low-thrust rocket engine for spacecraft attitude control and orbit correction.

1 5
TRL 9 · Flight-proven

Flight-proven UDMH/NTO bipropellant tank (40 dm³, 15 kg) for communication satellite KDU 11D414HC propulsion systems.

1 13

Formation of multiple impulses for attitude control of spacecraft in response to control system triggering commands.

1 10

Formation of multiple impulses for attitude control of spacecraft in response to control system triggering commands. Design features: - A high temperature Niobium alloy nozzle with disilicide oxidation resistant coating.

1 10
TRL 9 · Flight-proven

Flight-proven 13.3 N UDMH/NTO thruster (0.55 kg, 450,000 starts, Isp 2688 m/s) flown on MIR, ISS Zarya module, Briz, and Strela.

1 15
TRL 9 · Flight-proven

Ka/K-band 3-way branching filter (27/30/32.5 GHz, ≤0.9 dB insertion loss, ≥65 dB suppression) for antenna feed system paths.

1 10

Glavkosmos product — C-band Antenna which Forms Planimetric Directional Diagram. Details on request.

1 6
TRL 9 · Flight-proven

C-band passive band-pass filter (≤0.6 dB insertion loss, SWR ≤1.22) for antenna feed system paths.

1 4
TRL 6 · Prototype

C-band global-beam antenna (3.5–3.7 GHz, ≥20.2 dBi gain, 1105×455 mm, ≤7.5 kg, polymer composite material).

1 8
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (16–160 V, 680–22000 µF, -60 to +100 °C, screw terminals, low-impedance) for power electronics. 25-year life.

1 11
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (16–250 V, 47–6800 µF, -60 to +100 °C, wire terminals, low-impedance) for power electronics. 25-year life.

1 11
TRL 9 · Flight-proven

Sealed low-impedance aluminum electrolytic capacitor (6.3–450 V, 22–22000 µF, -60 to +100 °C, radial wire leads) for demanding conditions. 25-year life.

1 11
TRL 9 · Flight-proven

Sealed low-impedance aluminum electrolytic capacitor (16–100 V, 1500–100000 µF, -60 to +100 °C, radial screw leads) for high-capacitance applications. 25-year life.

1 11
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (6.3–450 V, 1–4700 µF, -60 to +100 °C, axial wire leads) with extended life at high electrical loads. 25-year life.

1 12
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (6.3–450 V, 1–15000 µF, -60 to +125 °C, axial wire leads, impact-resistant) with extended life. 25-year life.

1 12
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (63–450 V, 100–2200 µF, -60 to +125 °C, radial wire leads, impact-resistant, longitudinal crimping). 25-year life.

1 12
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (63–450 V, 470–4700 µF, -60 to +125 °C, radial wire leads, impact-resistant) for high-capacitance demanding applications. 25-year life.

1 12
TRL 9 · Flight-proven

High-reliability aluminum electrolytic capacitor (250–450 V, 100–680 µF, -40 to +85 °C, radial screw terminals, 100,000 hr derated life) for medical/industrial/railway.

1 13
TRL 9 · Flight-proven

High-reliability aluminum electrolytic capacitor (250–450 V, 470–15000 µF, -40 to +85 °C, 100,000 hr derated) for demanding power electronics. 25-year life.

1 13
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (6.3–450 V, 1–4700 µF, -60 to +100 °C, axial wire leads) substitute for K50-29/20/24/27. 25-year life.

1 12
TRL 9 · Flight-proven

Space-grade tantalum wet-slug capacitor (6.3–100 V, 15–680 µF, -60 to +85 °C) for spacecraft power supply modules.

1 12
TRL 9 · Flight-proven

Space-grade tantalum wet-slug capacitor (6.3–63 V, 47–2200 µF, -60 to +125 °C, 25-year life) for spacecraft power supply modules.

1 12
TRL 9 · Flight-proven

Space-grade tantalum wet-slug capacitor (6.3–125 V, 1.5–4700 µF, -60 to +125 °C, 25-year life) for spacecraft power supply modules.

1 12
TRL 9 · Flight-proven

Space-grade high-voltage tantalum wet-slug capacitor (100–200 V, 1.5–220 µF, -40 to +125 °C, 25-year life) for spacecraft power supply.

1 12
TRL 9 · Flight-proven

Space-grade high-temperature tantalum wet-slug capacitor (6.3–125 V, 6.8–470 µF, -60 to +175 °C, 25-year life) for spacecraft power supply.

1 12
TRL 9 · Flight-proven

Space-grade low-ESR tantalum wet-slug capacitor (63 V, 10–470 µF, -60 to +125 °C, 30-year life) for AESA charge-discharge applications.

1 12
TRL 9 · Flight-proven

Space-grade tantalum wet-slug capacitor (6.3–125 V, 1.5–1000 µF, -60 to +125 °C, 25-year life) for spacecraft power supply modules.

1 12

Tantalum solid-electrolyte capacitor for space, aviation and rocket electronics power supply modules.

1 8
TRL 9 · Flight-proven

Space-grade tantalum solid-electrolyte capacitor (6.3–20 V, 0.47–100 µF, -60 to +85 °C, 20-year life) for spacecraft power supply.

1 12
TRL 9 · Flight-proven

Space-grade SMD tantalum solid-electrolyte capacitor (4–50 V, 0.1–470 µF, -60 to +125 °C, 25-year life) with low ESR for weight-critical electronics.

1 12
TRL 9 · Flight-proven

Space-grade tantalum solid-electrolyte capacitor (6.3–50 V, 0.22–1000 µF, -60 to +125 °C, 25-year life) for spacecraft power supply.

1 12
TRL 9 · Flight-proven

Space-grade low-impedance SMD tantalum solid-electrolyte capacitor (2.5–50 V, 0.1–680 µF, ±5% tolerance, -60 to +125 °C, 25-year life).

1 12
TRL 9 · Flight-proven

Space-grade SMD tantalum solid-electrolyte capacitor (4–50 V, 0.22–680 µF, leakproof, -60 to +125 °C, 25-year life) for weight-critical electronics.

1 12
TRL 9 · Flight-proven

Space-grade non-polar tantalum solid-electrolyte capacitor (16/32 V, 0.1–47 µF, -60 to +85 °C, 25-year life) for spacecraft power supply.

1 12
TRL 9 · Flight-proven

Space-grade ultra-low ESR multianode tantalum solid-electrolyte capacitor (2.5–32 V, 22–1500 µF, -60 to +125 °C, 25-year life).

1 12
TRL 9 · Flight-proven

Aluminum electrolytic capacitor (6.3–450 V, 1–3300 µF, -60 to +105 °C, small size, high climatic resistance, enhanced low-temperature stability). 25-year life.

1 12
TRL 9 · Flight-proven

Import-substitution chip aluminum electrolytic capacitor (6.3–450 V, 1–10000 µF, -60 to +125 °C, SMD) replacing foreign high-voltage small-sized types. 20-year life.

1 12
TRL 9 · Flight-proven

High-reliability snap-in aluminum electrolytic capacitor (16–450 V, 47–47000 µF, -60 to +125 °C) for demanding power electronics. 20-year life.

1 12
TRL 9 · Flight-proven

Supercapacitor (2.7 V, 1–100 F, 15–200 mΩ ESR, -50 to +65 °C, fast charge, maintenance-free, no memory effect). For energy storage and backup power.

1 14
TRL 9 · Flight-proven

Launch vehicle ground support transport cart (up to 4000 kg, 6266 mm long, 3660 mm wide, 5–7 km/h tow speed). Manually or vehicle-pulled.

1 12

Technology for manufacturing mirror antennas of caisson type with reduced reflector surface density.

1 6

Charged particle detector was developed by Sputnix in collaboration with scientists from SINP (Moscow State Univercity). Detector provides simultaneous monitoring and single events parameters measurement. Recorded data can be accessed via satellite data bus.

1 10
TRL 9 · Flight-proven

Flight-proven ammonia CPS for orbit/attitude correction and flywheel momentum dump (5000–5500 N·s total impulse, 0.02–0.8 N thrust, ≤17 kg).

1 12
TRL 9 · Flight-proven

Spacecraft comprehensive electrical test complex (334 discrete outputs, 324 inputs, 18 DC channels, 20-ch solar simulator, 27 V/5 A supply, QNX/Windows). Customizable.

1 21
TRL 9 · Flight-proven

Spacecraft orientation system test complex (MIL-STD-1553B, magnetic field simulator, 42-ch signal monitoring, UPS, Windows) for ADCS testing. Customizable.

1 17
TRL 9 · Flight-proven

Radar complex for LV detachable part tracking (10 GHz, >300 km, variable 10°×10° to 1.25°×2.5° beam, weatherproof) for impact area raiding parties.

1 9
TRL 9 · Flight-proven

Flight-proven composite xenon/nitrogen storage tank (38.2 dm³, up to 71 kg Xe) for electric propulsion systems, 22-year service life.

1 13
TRL 9 · Flight-proven

Flight-proven composite pressure vessel (18 dm³, 5.8 kg) for pressurant storage and feed in the Phobos Sample Return Mission propulsion system.

1 14

Compressed Gases Storage Equipment (CGSE) includes 210 bottles, incorporated in 6 receiver blocks; nitrogen charging boards; air charging boards; nitrogen supply boards; air supply boards; helium charge and supply board; quality control board; hygrometer; oil indicator; gas pressure monitoring board

1

LV Compressed gases supply system (LV CGSS, CGSS) includes distribution boards; purging boards, auxiliary boards; supply boards; control boards; control pressure boards; panels; pressure sensor units; pressure gage panels; parameters monitoring boards; pressure reduction boards; quality control boar

1

Flight-proven CFRP conical adapter (650 mm) interfacing spacecraft to the Briz-M upper stage on Proton.

1 8

Flight-proven CFRP conical adapter (398.5 mm, 34 kg) interfacing spacecraft to the Fregat-SB upper stage on Zenit.

1 8

Conical grid-shell adapter providing the mechanical interface between a spacecraft and its upper stage.

1 7

Conical grid-shell adapter providing the mechanical interface between a spacecraft and its upper stage.

1 7

Conical grid-shell adapter providing the mechanical interface between a spacecraft and its upper stage.

1 7

Two-phase (vapor/liquid) hermetic closed evaporating/ condensing thermal transfer system filled with a working fluid (usually by Ammonia or Propylene). Small pipes diameter allows to bend transport lines that simplifies essentialy CHP integration into the spacecraft; Condensers of different design (

1 5

Programmable control complex of large-sized product forms in real time. The principle of operation is based on measurement of the product shape deviation from the a predetermined value using a network of compact triangulation distanse sensors, mounted on the stocks near the control points of the obj

1 7

The software package operation is limited to control of colour array of spacecraft structural function diagram, obtained as a result of proccessed telemetric data. In case of onboard system alarm state, an operator can analyze current situation using output ducuments or a graph of selected parameter

1

Software package featuring the following functions: -Virtual machine creation and control; - Distributed fail-safe storafe of virtual machines; - High availability of virtual machines and package elements; - Package automatic installation and setting; - Common control web-interface; - Terminal devic

1
TRL 9 · Flight-proven

Flight-proven cold-gas thruster (0.73–0.82 N He/N2, 0.105 kg, 80,000 starts) for precise spacecraft attitude control, flown on KOSMOS and RESURS-DK.

1 14

Consists of two units: Stationary Plasma Thruster with a nominal discharge power of 1350 W and Xenon Flow Controller Unit (XFC Unit). Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procured parts and components (6

1 10

The corrective propulsion system of the UD-AIPD consists of a monoblock, including the KNE block, the BIR1, BIR2 block, and the discharge accelerator channel. UD-AIPD includes a set of mounting parts. The operating mode of the UD-AIPD is pulse with a pulse repetition rate of 4 Hz.

1 7

Corrective propulsion system (CPS) consists of a monoblock, including an AIPD-95 CPS engine, a BPU-150 device, a set of mounting parts. The CPS AIPD-95 engine includes a KNE block, a BIR1, BIR2 block. CPS AIPD-95 is equipped with KIA CPS. The operating mode of the AIPD-95 CPS is pulsed with a pulse

1 7
TRL 9 · Flight-proven

Heavy-lift crossbeam for transshipment of long loads with variable center of mass (up to 90 t, 16.5 m length, 10.0 t crossbeam mass). Customizable.

1 11
TRL 9 · Flight-proven

Precision crossbeam for spacecraft mating operations (up to 1.0 t load, 180 kg mass) with kinematic load compensation device. Customizable.

1 10
TRL 8 · Qualified

CubeSat 3U ADCS functional test bench (air bearing, sun simulator, magnetic field simulator, autonomous measurement system, 5000×3000×2500 mm, 250 kg) for orientation testing.

1 16
TRL 9 · Flight-proven

Amateur-band cubesat ground station (UHF 435–438 MHz, 9600 bps, AX.25/FSK, rotating directional antenna + 2 fixed survey antennas, 4 W Tx, SDR-based).

1 13

Radiation-resistant secondary DC/DC converter on switched capacitors, similar to TPS605000/LM2771/LTC3250.

1 8

Large deployable mesh-type reflector antenna component, 4.2 m aperture, flight-qualified for spacecraft communications systems.

1 6
TRL 5 · Development

Large flat antenna deployment mechanism (3×100 m aperture, ≤1200 kg, ≤Ø4450 mm stowed, ±0.015° pointing, 5 mm flatness on orbit).

1 11

It is made according to "Regulation 88". Version: piezoelectric transducer, consisting of a sensitive element installed in the housing, and a matching device connected by a cable jumper. Explosion protection type - "Intrinsically safe electrical circuit" - is provided by an intermediate converter.

1 5

It is made according to the "Regulation 98". Version: piezoelectric transducer, consisting of a sensor installed in the housing, a flexible cable and a connector. Explosion protection type - "Intrinsically safe electrical circuit" - is provided by an intermediate converter.

1 5
TRL 4 · Development

Radiation-resistant 3-channel digital isolator prototype (20 Mbps, USB/CAN/RS-485/RS-232/SPI/I2C galvanic isolation, 3–5 V, 1.5 kW). 12-month delivery.

1 10

High performance digital signal processor. The processor architecture is based on the use of the new generation VLIW / SIMD processor core NMC4. The processor contains two processor cores NMPU0 and NMPU1, each of which includes a RISC processor and a vector coprocessor.

1 7
TRL 9 · Flight-proven

Flight-proven Ka-band double-mirror parabolic antenna (20 GHz, Ø1800 mm reflector, ≤0.3 mm rms surface, 10.5 kg, CFRP).

1 9

Dual operating mode: 1.35 / 2.5 kW. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and four external magnetic coils. Outside diameter of the accelerating channel is 100 mm. Mean diameter of the accelerating channel is 85 mm.

1 10

Version: strain gauge sensor with cable jumper. Upon customer's request, it is made with a screwed fitting and a collar (Ø32) for welding or only with a screwed fitting. The type of explosion protection of the sensor is “Tight sheath”, cable jumper - “Intact cable network”.

1 5

The System consists of pneumoboards; pressure indicator unit; pressure sensor unit; drainage pneumoboard; three manifolds; set of pipelines and valves.

1
TRL 9 · Flight-proven

Flight-proven single-stage normally-closed solenoid valve (1.6 mm, 2.45 MPa, 505,000 cycles) for liquid/gaseous propellant flow control.

1 14

EH is a flexible single-sided printed circuit board on a thin, dielectric base made of fiberglass or polyimide film with a resistive printed conductor made of manganin foil of a certain configuration deposited on it. A protective dielectric coating of a polyimide film or varnish is applied over the

1 5

The electric heater is a flexible single-sided printed circuit board on a thin, dielectric base made of fiberglass with a resistive printed conductor made of manganin foil of a certain configuration deposited on it. A protective electrical insulating coating is applied over the conductor.

1 5

Electric propulsion. It has high specific impulse at relatively low power. The record number of burnings is up to 20000 cycles.

1 5
TRL 7 · Demonstrated

Hall-effect electric thruster (95 mN, <2.4 kW, Isp 2680 s, 5.25 kg) for 2500–3000 kg spacecraft, record specific impulse.

1 13
TRL 8 · Qualified

High specific impulse Hall thruster (72 mN, 1.65 kW, Isp 2680 s, 6 kg) for 3000 kg spacecraft; flight set delivered.

1 14
TRL 9 · Flight-proven

Flight-proven multimode Hall thruster (80/115 mN, 1.35/2.0 kW, Isp >1550 s, 5.2 kg) flown on Express-A4 (2002).

1 14
TRL 9 · Flight-proven

Flight-proven low-power Hall thruster (18 mN, 350 W, Isp 1450 s, 2 kg) for small spacecraft ≤500 kg; flown on GSAT-9 (2017).

1 13
TRL 6 · Prototype

High-power sustainer Hall thruster (520 mN, 10.5 kW, Isp 2580 s, 11.8 kg) for spacecraft transportation missions.

1 13
TRL 6 · Prototype

Spacecraft water electrolysis oxygen supply unit (30 kg, 99.9% purity, 25–160 L/h, 10–70 A, zero-gravity capable, solid polymer membrane).

1 12

The core electromagnet for the stabilization equipment of the spacecraft with a harness on which the connector is soldered.

1 4

Electromagnetic unit (EMU) - Magnetic Torquer There is an option to develop and supply EMU with magnetic moment from 0.2 to 800 А·m² according to customer requirements

1 9

Electromagnetic unit (EMU) - Magnetic Torquer for nanosatellites. There is an option to develop and supply EMU with magnetic moment from 0.2 to 2 А·m² according to customer requirements.

1 9

Includes: GLONASS/GPS receiver with antenna, 406.037 MHz and 121.5 MHz transmitters, the voice communication device (121.5 MHz radio station), AНT-AРM-2 antenna, the liquid crystal indicator for displaying position data and service information, highlight, self-contained power source (battery, accumu

1 5

Glavkosmos product — Equipment for determing the center-of-mass position and inertia characteristics of nanosatellites. Details on request.

1 2
TRL 9 · Flight-proven

Flight-proven head fairings for Soyuz (Ø3715 mm) and Zenit (Ø4100 mm) launch vehicles (1180–1870 kg) for spacecraft aerodynamic/thermal protection during ascent.

1 8
TRL 9 · Flight-proven

Ka-band feed cluster for Ku multiple-beam antenna (28 horn cluster in 3 zones, 13 kg) with polarization selector, diplexer, and thermal decoupling.

1 8
TRL 9 · Flight-proven

C-band antenna feed (16 kg, crimped horn with polarization device) for spacecraft antennas forming planimetric directional diagrams.

1 6
TRL 9 · Flight-proven

Ku-band antenna feed (6 kg, crimped horn with polarization selector, diplexer, splitter) for large antenna systems with planimetric beams.

1 5

Elements of antenna feed system and flight communication equipment paths of different frequency bands.

1 6

Version: strain gage sensor, consisting of a cylindrical type elastic element, strain gages connected in two bridge circuits, a casing, a power input unit and a plug. Type of protection - “Intrinsically safe electrical circuit” - is provided by an intermediate converter.

1 5

Uses GaAs photo-electric converters and has built-in electromagnetic coils. Features: There is a 13 mm diameter aperture at the panel center with M2 mount holes for sun sensors or similar payloads.

1 10
TRL 9 · Flight-proven

Flight-proven GaAs side solar panel for CubeSats with built-in electromagnetic coil for attitude stabilization, 28% efficiency.

1 19
TRL 7 · Demonstrated

Xenon gas feed unit regulating flow (0.2–1.2 g/s) and pressure (1.7 ± 0.17 kgf/cm²) to electric orbit control thrusters.

1 13
TRL 9 · Flight-proven

Flight-proven Buran-heritage spacecraft cockpit glazing (700 K operation, ≥150 MPa compression stress, double-chamber, optical quality). Customizable.

1 11

The navigation receiver is designed to calculate the current coordinates and speed of an object in real time in stand-alone and differential modes, form a second time stamp and exchange information with external equipment using RS232 interfaces. It is an electronic module of zero level in accordance

1 29
TRL 9 · Flight-proven

GPS+GLONASS L1 navigation receiver in secure case (16 ch, 9 m CEP, 2×RS-232, 71×51×12 mm, 50 g, -40 to +85 °C, 0.65 W). For mission-critical applications.

1 30

The receiving dual-band mirror antenna system is built on the Cassegrain system, includes an antenna with a reflector of 2.5 m, two replaceable irradiating systems of the C and Ku bands, and a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transm

1 9

The transmitting two-mirror antenna system is built on the Cassegrain system, it includes an antenna with a reflector of 2.5 m with an irradiating system and a counter-reflector, and a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting d

1 7

The receiving two-mirror antenna system is constructed according to the Cassegrain system, it includes an antenna with a 12.0 m reflector with replaceable irradiators and a counter-reflector, a slewing ring with electromechanical drives. Remote polarization switching. Replaceable irradiators: C-band

1 8

The transceiver two-mirror antenna system is built on the Cassegrain system, includes an antenna with a 2.4 m reflector with an irradiating system and a counter-reflector, and a slewing gear with manual drives. The structure does not include radio receivers and radio transmitting devices.

1 9

The transceiver two-mirror antenna system is built on the Cassegrain system, includes an antenna with a 6.0 m reflector with an irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transmitting devices.

1 10

The transceiver two-mirror antenna system is constructed according to the Cassegrain system, it includes an antenna with a 6.0 m reflector with a dual-band irradiating system and a counter-reflector, a slewing ring with electromechanical drives. The structure does not include radio receivers and rad

1 10

The receiving dual-band mirror antenna system is built on the Cassegrain system, includes an antenna with a reflector of 2.5 m, two replaceable irradiating systems of the C and Ku bands, and a slewing ring with electromechanical drives. The structure does not include radio receivers and radio transm

1 9
TRL 9 · Flight-proven

Spacecraft control ground station (VHF/UHF 140–450 MHz, 18/8 dBi, 20 W, 9600–38400 bps, 2°/s tracking). Flight-qualified. Customizable.

1 15

Redundant free form gyroscopic angular velocity vector meter for spacecraft orientation and stabilization control system. Sealed monoblock device, including electronic and optoelectronic modules with a block of four sensitive elements of a fiber-optic gyroscope and four sensitive elements of pendulu

1 9

Redundant free form gyroscopic angular velocity vector meter for spacecraft orientation and stabilization control system. Sealed monoblock device, including electronic and optoelectronic modules with a block of four sensitive elements of a fiber-optic gyroscope and four sensitive elements of pendulu

1 9

Monoblock device includes electronic and optoelectronic modules and a block of sensitive elements containing three mutually orthogonal sensitive elements of a fiber-optic gyroscope.

1 5

Redundant free form gyroscopic angular velocity vector meter for spacecraft orientation and stabilization control system. An unsealed two-block construction including an electronic device unit with four independent channels consisting of electronic and optoelectronic modules and an inertial unit con

1 4
TRL 9 · Flight-proven

High-precision harmonic drive for antenna pointing (Ø85 × 23.5 mm, ±40 arcsec transfer error, 200,000 rev life, 15-year GEO).

1 10
TRL 9 · Flight-proven

High-precision harmonic drive for antenna pointing (Ø85 × 34 mm, ±30 arcsec transfer error, 200,000 rev life, 15-year GEO).

1 10
TRL 9 · Flight-proven

Flight-proven P/L/S-band helical on-board antenna (conical/cylindrical/convertible frame, fiberglass/organic plastic, fixed/varied pitch). Customizable.

1 10
TRL 9 · Flight-proven

RTK/GNSS high-precision navigation module (GPS/GLONASS/Galileo, <0.01 m RTK, <0.2 m standalone, 9–36 V, 120 g, -40 to +85 °C). For automotive/transport applications.

1 16
TRL 9 · Flight-proven

Spacecraft pneumatic electric valve for high-pressure gas paths (up to 250 kgf/cm²), 15.5-year active lifetime, 0.25 W holding power.

1 11

High voltage power supply system kit KPVS includes: The ability to configure the power supply system for power from 2 to 60 kW by increasing or decreasing the number of modules. It is planned to operate as part of the scientific and energy module of the International Space Station (ISS).

1 4

Glavkosmos product — High-capacity Rechargeable Battery for Power Supply of Spacecraft and Ground Infrastructure. Details on request.

1 9
TRL 7 · Demonstrated

Multimode Hall thruster (200/380 mN, 3.5/6 kW, Isp 1700/2650 s, 8 kg) for 3000 kg spacecraft, qualification model.

1 14
TRL 9 · Flight-proven

Flight-qualified angle-setting complex (0–360°, ±0.5° error, 0.013° resolution, auto self-calibration, ≤65 kg load) for gyros, accelerometers, and angle sensors in rocket/space systems.

1 18
TRL 9 · Flight-proven

Flight-proven X-band downlink transmitter (800 Mbps, 8 W, 1.8 kg, 70 W, ISS/AIST-2D heritage, >6 krad radiation tolerance).

1 15
TRL 9 · Flight-proven

Launch facility propellant supply system for LV stage tank filling/discharge with high-strength hydrogen peroxide. Pipeline-based, launch-facility-integrated.

1 9

Honeycomb panels with composite face sheets, with fixed or attachable heat transfer tubes or fluid loops. Off-the-shelf efficient solutions include standard series of honeycomb fillers and face sheets, filling blocks; possibility of installing heat transfer tubes or fluid loop tubes; mounting of opt

1 6
TRL 9 · Flight-proven

C/Ku/Ka-band spacecraft horn antenna (Ø410 mm × 1100 mm deployed, smooth conical/crimped/modified, aluminium/brass/CFRP construction).

1 6

Mobile Hydrogen Peroxide Tanker includes vessels for high-concentrated hydrogen peroxide (HCHP), vessel for demineralized water, vessel for industrial water, electric equipment, pneumatic and hydraulic equipment, HCHP temperature and volume control means, compressed air bottles, stop valves.

1 3

Sealed monoblock device including electronic and opto-electronic modules with a block of sensitive elements, containing three mutually orthogonal sensitive elements of fiber-optic gyroscopes and three of mutually orthogonal sensitive vibrating string accelerometer elements.

1 2

28 nm CMOS heterogeneous computing microcircuit with ARM Cortex-A5 core for real-time video, radar and neural-network processing.

1 6
TRL 8 · Qualified

High-performance VLSI MIVEM multimedia SoC (CMOS 28 nm, HFCBGA-1024, 800 MHz PowerPC + 400 MHz NMC3, -50 to +70 °C) for onboard video/audio processing and ARINC 818.

1 13

ITU-5000M includes a high-precision Thruster Orientation Mechanism (TOM) and a propulsion system based on the Modified Stationary Plasma Thruster with a discharge power of up to 5 kW. Each propulsion system consists of a thruster and a XFC Unit, pneumatic connections between which are realized by me

1 8

Integrated Thruster Unit (ITU) includes a high-precision thruster orientation mechanism (TOM) and two propulsion systems based on the stationary plasma thruster with a nominal discharge power of 1350 W. Each propulsion system consists of a thruster and a Xenon Flow Controller Unit, pneumatic connect

1 8

A stand with mechanical drive, which allows to to set the angle of inclination of the Product in any position with high accuracy.

1 4
TRL 9 · Flight-proven

Spacecraft integration platform (10200 kg, 4230×16035×10505 mm) with 3-level service platforms for assembly/disassembly and solar panel deployment testing.

1 12
TRL 9 · Flight-proven

Vehicle telemetry interface module (120×90×40 mm, 120 g, 9–36 V, <4 W) with RS-485/232/CAN/USB, 8 digital + 4 analog inputs, black-box memory.

1 20

Optical communications equipment for work in the constellation of satellites at the same height. Monoblock design. Adaptation to any platform with a weight of 300 kg.

1 9

Optical communications equipment between satellites on LEO and between LEO and Earth. Adaptation to any platform with a weight of 400 kg.

1 9
TRL 9 · Flight-proven

Spacecraft automated electrical test complex (Ethernet/MIL-STD-1553B, 29-ch pulse + 18-ch long-term command outputs, 67-ch on-off monitoring, magnetic field simulation, QNX/Windows). Customizable.

1 17

Glavkosmos product — Ka-band Antenna for the Locator Beacon Signal Transmission. Details on request.

1 5
TRL 6 · Prototype

Ka/Q-band high-precision mirror antenna (Ø800 mm, ≤0.3 mm rms surface, 6.3 kg, high-modulus CFRP) for GEO missions. Customizable.

1 9
TRL 9 · Flight-proven

Launch facility kerosene pre-cooling system (85 t storage, -196 °C coolant, -3 °C kerosene min temperature) for LV stage propellant conditioning.

1 11
TRL 9 · Flight-proven

Launch facility pipeline system for LV third stage tank kerosene supply/discharge. Spans launch facility and MST. Customizable.

1 10
TRL 9 · Flight-proven

Launch facility pipeline system for LV first/second stage tank kerosene filling/dumping. Launch-facility-integrated. Customizable.

1 10
TRL 9 · Flight-proven

Flight-proven magnetic torquer assembly (6 × 1000 Am² rods, 50 kg, 50 W) for low-orbit spacecraft momentum unloading.

1 13

Kinetic moment reset system. Structurally, the product consists of: - 2 primary converters of the geomagnetic field PGP-3M, PGP-3MD (duplicate); - 3 electromagnets (length - 0.85 m), forming three axis rod electromagnets; - electronic block.

1 4
TRL 9 · Flight-proven

Flight-proven Ka-band multiple-beam spacecraft antenna (15-year life, 15-month delivery) in flight operation since launch.

1 7

Attenuator (ATT) is designed to control the amplitude of the input signals of the L-band. The MMIC is developed on the basis of silicon-germanium BiKMOS technology. MMIC ATT is a parallel-serial chain of resistive blocks, switched using MOS keys. An amplifier has been added to the circuit to obtain

1 12

MMIC phase shifter (PS) controls the phase of the input signals of the L-band. MIS is developed on the basis of silicon-germanium BiKMOS technology. The basis of the MIS FV circuit design is the vector addition of orthogonal signals. MMIC has differential inputs and outputs. Phase states are control

1 14

SiGe (Silicon-germanium) BiKMOS microwave MMIC mixer implements the Gilbert active mixer circuit. The microcircuits are designed to operate as a mixer of the receiving and transmitting paths in the frequency range up to 2 GHz, with a possible extension of the band to 4 GHz.

1 14

MMIC LNA is designed for equipment with severe restrictions on the level of power consumption, including: Due to the capabilities of BiKMOS circuitry and the high speed of silicon-germanium transistors, silicon-germanium BiKMOS microwave MMIC LNA has significantly lower power consumption compared to

1 12

polarization selection of received signals and forming required polarization of the radiated signals

1 4

Long-focus lens objective (500 mm aperture, 4000 mm focal distance) for Earth remote sensing equipment.

1 8

LS is a metal structure on which the equipment as follows is assembled: 4 Frames for ILV weight load taking; 4 Frames for ILV holdup when wind forcing; 2 Masts for supply lines connexion to ILV. Inside the frame basements the sets of electric and hydraulic equipment for the Frames motion provision a

1

Short-focus lens objectives (40 mm aperture, 40-200 mm focal distance) for Earth remote sensing payloads.

1 8

Wide-angle 13-lens objective for detection of low-orbit space objects at altitudes from 120 to 500 km.

1 12

High precision electromechanical drive of linear positioning. 2 commutator electric motors (1 is in reserve).

1 8

System includes tanks, pipelines, valves and control means located in different facilities of Launch Complex.

1 3
TRL 9 · Flight-proven

Launch facility LOX intake/storage/delivery system (672 t storage, -183 °C, 191 t LV delivery) for LV oxidizer supply.

1 11

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 10

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 10

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 11

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 11

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 11

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 11

Cylindrical CFRP grid-shell load-bearing structure for mounting spacecraft subsystems and equipment.

1 10
TRL 9 · Flight-proven

Ultra-lightweight (40 g) spacecraft electric valve for high and low pressure gas paths (up to 250 kgf/cm²), low-emission design.

1 11
TRL 9 · Flight-proven

Low-pass filter for antenna feed system paths (SWR ≤1.15, ≤0.15 dB insertion loss).

1 4

Plasma thruster. Propellant - xenon. Consists of the anode and cathode units. With hollow cathode. Development status – engineering model. Mean diameter of the accelerating channel is 34 mm. New structural materials and components. Manufacturing lead time is given without taking into account the tim

1 10

Thruster. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and three external magnetic coils. Outside diameter of the accelerating channel is 50 mm. Mean diameter of the accelerating channel is 40 mm. Manufacturing lead time i

1 10

Thruster. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and four external magnetic coils. Outside diameter of the accelerating channel is 70 mm. Mean diameter of the accelerating channel is 55 mm. Manufacturing lead time is

1 10
TRL 9 · Flight-proven

Spacecraft electric valve for low-pressure gas paths (up to 5 kgf/cm²), 15.5-year active lifetime, 0.25 W holding power.

1 11
TRL 9 · Flight-proven

Flight-proven ammonia heat pipes (-30 to +60 °C, ≤5 °C ΔT, up to 500 W) for spacecraft thermal control. Heritage: Meteor, Intercosmos, Electro, Coronas.

1 11

Devices are used as switchboards, power distribution points, control and automation panels and cabinets, and as switchboards on the undervoltage side of packaged transformer stations.

1
TRL 9 · Flight-proven

High-pressure (38–40 MPa) compressed air/nitrogen intake and delivery system for LV thermal conditioning. Components: pneumoboards, cooler, heater, supply pipelines.

1 6
TRL 9 · Flight-proven

Stationary LV compartment thermal conditioning system (air cleaning/drying/heating) for Soyuz at Kourou, GSC launch complex. Vapor compression refrigerating machine.

1 8

System of three pairs of square coils mutually orthogonal to each other (Helmholtz cage) simulates the magnetic field as it changes during the orbital flight the satellite. By inducing current in coil’s wires the magnetic field is created and its direction and value depend on the amperage. Currents

1 3

Device for manual start-up of pico and nanosatellites from International Space Station (ISS). Supplied with remote control. There is an option to develop and supply a launch device for automatic launch in any orbit.

1 8

Leak is determined by the helium flow penetrating into the tested volume during the vacuum test, or by the flow of helium going from the tested volume at a excessive pressure in it.

1 10
TRL 7 · Demonstrated

Uncased microwave varactors on thin membrane (1–500 pF, >50 GHz, >40 V breakdown, 15 µm thickness, 0.003 g) for AESA phase shifters in space/aviation systems.

1 12

T-406Н КС tester represents a compact portable device. T-406Н КС tester is able to receive radio signals both over the air, when antenna is attached, and over coaxial cable. Self-contained power is supplied by built-in rechargeable battery with the total voltage equal to (3.7 V ± 10%) and capacity n

1 5
TRL 9 · Flight-proven

Electromechanical hold-down and release device (1000 kg clamping force, 0.455 kg, 50 actuations, 3–8 A actuation current).

1 12
TRL 9 · Flight-proven

2-DOF electromechanical antenna pointing drive (±25° per axis, 65 N·m, 150 kg·m² load inertia, 10-year life).

1 13
TRL 9 · Flight-proven

2-DOF electromechanical antenna pointing drive (±25° per axis, 30 N·m, 3 kg·m² load inertia, 10-year life).

1 13
TRL 9 · Flight-proven

2-DOF electromechanical antenna pointing drive (±10°/±90° per axis, 60 N·m, 15-year life) for GEO missions.

1 13

Two-degree-of-freedom electromechanical drive for antenna pointing. Operating regimes: tracking, pointing.

1 10
TRL 9 · Flight-proven

200-litre flight-proven metal-composite xenon tank (350 kg Xe, 28 kg, 15.5-year lifetime) for GEO electric propulsion orbit-raising.

1 14
TRL 9 · Flight-proven

350-litre flight-proven metal-composite xenon tank (up to 570 kg Xe, 43.5 kg, 15.5-year lifetime) for GEO electric propulsion orbit-raising.

1 14
TRL 4 · Development

Radiation-resistant micropower 10-bit SAR ADC prototype (1 MSps, 16-ch multiplexer, SPI, 3–5 V, <1 mA, -60 to +125 °C). Similar to AD7490/AD7475. 12-month delivery.

1 15

Silicon-Germanium BiKMOS VLSI is designed to produce a stable high-frequency signal in the 375-6000 MHz range with a low level of phase noise and a small tuning step without using an external VCO. Functional Analog: ADF4350 (Analog Devices Inc.)

1 13
TRL 7 · Demonstrated

Uncased microwave p-i-n switching elements on thin membrane (>50 GHz, >50 V Vbr, 5 Ω Ron, 5–20 µm membrane) for AESA phase shifters in space/aviation systems.

1 12
TRL 9 · Flight-proven

Flight-proven C/Ku/Ka-band offset reflector antenna (Ø600–1200 mm, paraboloid of rotation cut, single/multi-beam horn feed). Customizable.

1 8

Component of the mirror antenna. If required mounting reflector on the boom is available Reflectors have areas for hold-down locks and are equipped with optical checking elements.

1 6

Large-dimensioned mirror-lens objectives. Item is produced in accordance with the Customer's working design documentation (WDD).

1 2
TRL 9 · Flight-proven

Ka-band MLS input filter (25340 MHz center, ≤1.4 dB insertion loss, ≥20 dB reverse losses, ≤1 W, 15-year life).

1 9
TRL 6 · Prototype

Ka-band MLS input filter (25980 MHz center, ≤1.4 dB insertion loss, ≥20 dB reverse losses, ≤1 W).

1 7
TRL 6 · Prototype

Ka-band MLS input filter (26620 MHz center, ≤1.4 dB insertion loss, ≥20 dB reverse losses, ≤1 W).

1 7

The station includes an antenna system with a 2.4 m Ku-band reflector. The design is collapsible, transported in containers from the station. It provides point-to-point communication through the Luch spacecraft.

1 10

MST is a mobile weather-proof and self-propelled structure, which can travel inside the launch facility on two parallel railway tracks consisting of two rails each due to traveling gear representing four self-propelled balance trucks. MST is equipped with the gates at its front and rear ends, statio

1 2

Passive glass retroreflector spherical satellite used to calibrate quantum-optical ground stations.

1 3

Thruster. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and three external magnetic coils. Outside diameter of the accelerating channel is 50 mm. Mean diameter of the accelerating channel is 40.5 mm. Low flow rate cathode.

1 10

In terms of discharge power it has been forced up to 1250 W. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system of armored type with magnetic screens. Outside diameter of the accelerating channel is 70 mm. Mean diameter of the accelerating channel is

1 10

Thruster with a discharge power of up to 5 kW. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and eight external magnetic coils. Outside diameter of the accelerating channel is 140 mm. Mean diameter of the accelerating chann

1 10

Thruster with a nominal discharge power of 1350 W. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and four external magnetic coils. Outside diameter of the accelerating channel is 100 mm. Mean diameter of the accelerating ch

1 10

Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid valves that supply propellant to the thruster, and a pressure signaling indicator that monitors the fact that the thruster

1 10

Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid valves that supply propellant to the thruster, and a pressure signaling indicator that monitors the fact that the thruster

1 8
TRL 9 · Flight-proven

Flight-proven UDMH/NTO monopropellant tank (30.8 dm³, 5.2 kg) for Phobos Sample Return Mission return spacecraft propulsion.

1 14
TRL 9 · Flight-proven

Flight-proven Raspberry Pi Compute Module sensor carrier board (55 g, CAN, 0.25 W) for nanosatellites; flown on SiriusSat-1/2.

1 17
TRL 6 · Prototype

Raspberry Pi Compute Module nanosatellite OBC+ADCS carrier (60 g, CAN/I2C/SPI/UART, -40 to +60 °C) with integrated ADCS controller.

1 17
TRL 9 · Flight-proven

Flight-proven Raspberry Pi Compute Module nanosatellite OBC (59 g, CAN/I2C/SPI/UART) with sensor suite; flown on SiriusSat-1/2.

1 17

Bellows are manufactured of corrosion-resistant and fire-resistant steel grades 08Х18Н10Т or 12Х18Н10Т. They provide complete leak-tightness at high pressures and temperatures in combination with excellent flexibility, which is particularly important for hazardous industries.

1 5

Strength and thermal honeycomb panels with Aluminum and carbon fibre skins and honeycombs made of Aluminum foil. Thermal honeycomb panels contain embedded and manifold heat pipes, liquid loops, thermal optical coatings of different types, heaters, thermal sensors, multi-layer insulation.

1 3

Multi-layer honeycomb panels with fixed or attachable heat transfer tubes or fluid loops. off-the-shelf efficient solutions include standard series of honeycomb fillers and face sheets, filling blocks; possibility of installing heat transfer tubes or fluid loop tubes; mounting of optical solar refle

1 4
TRL 5 · Development

Multi-zone space furnace for ISS semiconductor crystal growth experiments (up to 1200 °C heater temperature, multi-zone workspace, 2-year life). Customizable.

1 7
TRL 5 · Development

High-power multichannel electric thruster (up to 600 mN, 5–10 kW, Isp 1500–4000 s, 12 kg) for spacecraft propulsion systems.

1 11
TRL 8 · Qualified

CMOS 28 nm SoC multicontroller (HFCBGA-676, Cortex-A5 600 MHz, CAN/MKIO/UART/GbE/ARINC-429/SPI/PCIe 2.0/DDR3, -60 to +85 °C) for onboard control systems.

1 13

Component of the mirror antenna. A feed of this type as a component of the offset mirror antenna provides formation of the narrow beams set for the specified servicing area in order to enhance signal for the specified subscribers.

1 5
TRL 6 · Prototype

Dual-channel magnetic torquer driver board for nanosatellites, controlling external magnetic coils in solar panels (PWM, 3 W peak, PC104).

1 15
TRL 6 · Prototype

4-cell nanosatellite battery pack (3200 mAh, 14.8 V) with overcurrent, overcharge and overdischarge protection.

1 13
TRL 8 · Qualified

Nanosatellite/onboard system debug board (JTAG/PDI/UART/I2C, USB to PC, galvanic isolation, solar cell channel, LED indicators, 3.3/5 V, 1-year life). Customizable.

1 14
TRL 6 · Prototype

Nanosatellite EPS board that collects power from solar cells and distributes it to onboard systems via constant and switchable channels.

1 14

Ground-based nanosatellite engineering model for developing and testing scientific payloads, software and onboard systems.

1 8
TRL 6 · Prototype

Triple-core nanosatellite OBC (AVR + M0 + M4F, 200 MHz, 32 GB microSD, 9-DOF IMU, CAN/I2C/UART/SPI interfaces).

1 16
TRL 6 · Prototype

Modular nanosatellite bus for spacecraft separation control, in-orbit monitoring, Earth remote sensing and space-debris/precursor detection missions.

1 18

SamSat 3U CubeSat platform for scientific and technological experiments, with ~2 dm³ of payload volume.

1 13
TRL 6 · Prototype

Nanosatellite solar cell board converting light into electricity, with optional integrated temperature/light sensors and magnetic coil.

1 14
TRL 6 · Prototype

VHF/UHF nanosatellite TT&C transceiver (144/433 MHz, AX.25, 9600 bps, PC104/original bus, I2C, SMA). Customizable.

1 14
TRL 9 · Flight-proven

ERA-GLONASS/GNSS vehicle telematics module (48 ch, GPS+GLONASS, GSM/UMTS, accelerometer, RS-485/232, 9–36 V, 120 g, -40 to +85 °C, <8 W).

1 19

The Systems includes pneumovalve unit; purge and pressure control board; control pneumoboard; pressure indicator and sensor board.

1

Equipment Set consists of: - set of power connectors; - set of cables and low-voltage packaged devices.

1 2
TRL 9 · Flight-proven

Flight-proven C/Ku/Ka/Q-band offset mirror antenna (Ø180–1800 mm, paraboloid/elliptic/contour reflector, 15-year life). Efficient complex interface manufacturing.

1 10
TRL 9 · Flight-proven

Multi-constellation GNSS board module (44 ch, GPS/GLONASS/Galileo/SBAS L1, 2.5 m 2Drms, 2×RS-232/LVCMOS, 71×51×12 mm, 10 g, 0.07 W). 4 hardware versions.

1 30
TRL 5 · Development

Deployable 5 m aperture high-precision antenna for deep space (≤0.02 mm deployment repeatability, stows in Ø1.9 m × 2.75 m). Customizable.

1 9

The On-board Memory Unit is designed to provide data storage for the remote sensing satellites payloads.

1 7

Infrared instrumentation for measuring the spectra of outgoing thermal radiation of the surface-atmosphere system with high spectral resolution in the interests of operational meteorology and climatology.

1 10

Cerium-doped optical glass cover plate protecting solar cells from outer-space radiation and environmental factors.

1 3

Ground contact point with spacecraft at LEO. Mobile design, placement on roofs of buildings and other non-specialized objects is possible. Mobile and stationary performance, adaptation for any support.

1 9

Glavkosmos product — Optoelectronic system of detection and measurement of space debris motion. Details on request.

1 6
TRL 9 · Flight-proven

Flight-proven P-band global-beam antenna (401.5–406.1 MHz, ≥15 dBi gain, 4 helical radiators, 10 kg, polymeric composite). Customizable.

1 10

The vacant area of the board is 2.54mm pitch breadboard where user can place any needed components to enable payload’s sensors and other periphery. Holds a MCU with CAN driver, which grants access to the satellite bus. The possibility to modify hardware and software by the customer.

1 9
TRL 8 · Qualified

CMOS 130 nm PCIe 1.1 physical interface chip (МК8306-144-1, -60 to +85 °C, type-5 acceptance) for high-speed interface modules. For aviation/space applications.

1 12

Comprises: GLONASS/GPS receiver with an antenna, ПРД-406 transmitter, ПРД-121 transceiver, AНT-AРM-02 transmitting-receiving antenna, the indicator for position and service data displaying, self-contained power supply, rechargeable battery, and charger. The radio beacon can be completed with hermeti

1 5
TRL 6 · Prototype

PMT-175 photomultiplier tube (220–650 nm, 10 mm cathode Ø, SbKCs, ≤50 µA/lm, 1.5 ns rise time, 14-dynode) for multispectral research.

1 17
TRL 6 · Prototype

PMT-186 photomultiplier tube (260–750 nm, 10 mm cathode Ø, 22 mm device Ø, ≥80 µA/lm, ≤1.5 ns rise time, SbKNaCs, 14-dynode). Customizable.

1 18

PMT-188 has bialkali photocathode and one-cascade multiplication system. The input window is made of boron-silicate UV glass.

1 10

PMT-tetrode has a bialkali photocathode and two-cascade multiplication system. The input window is made of boron-silicate UV glass

1 10

Version: piezoelectric sensor, consisting of a sensor installed in the housing, and a flexible cable.

1 5

Version: forced-cooling piezoelectric sensor, consisting of a sensor installed in the housing and a flexible cable.

1 5

Platform for cubesat 3U satellite installation contains all necessary items for entire microsatellite integration to provide its tests via test bench. Platform consists of structure and balancing system.

1 2
TRL 8 · Qualified

Air-bearing test platform for TabletSat microsatellite ADCS device integration and testing (structure, power supply, balancing, data Tx/Rx). Not customizable.

1 7
TRL 8 · Qualified

Air-bearing test platform for full TabletSat microsatellite (≤40 kg, 150 Wh battery, 2/5 V outputs, manual/auto balancing, data Tx/Rx). 5-month delivery.

1 11

The navigation receiver 14Ц820 is intended for the provision of solving the special-purpose coordinate-time tasks in-the-field.

1 6
TRL 9 · Flight-proven

Diesel power module (380/220 V, 20–600 kW) for mobile temperature control units during spacecraft transportation. Ship-container form factor. Customizable.

1 10

Power supply system uses power supply unit for power control in assistance with battery unit for energy storage and up to 14 solar panels as electrical source.

1 10
TRL 9 · Flight-proven

Pneumatic pressure alarm unit generating an overpressure warning signal at 4.5 kgf/cm², 15.6-year active lifetime.

1 9
TRL 9 · Flight-proven

Pneumatic pressure reducer for xenon/propellant feed lines, reducing 250 to 1.75 ± 0.1 kgf/cm², 0.15 kg, 15.5-year lifetime.

1 10
TRL 9 · Flight-proven

Pneumatic pressure reducer for propellant feed lines, reducing 250 to 2.6 ± 0.12 kgf/cm², 0.15 kg, 15.5-year lifetime.

1 10
TRL 9 · Flight-proven

Pneumatic pressure reducer for pressure integrity check units, reducing up to 140 to 1.7 ± 0.17 kgf/cm², 0.15 kg.

1 10
TRL 9 · Flight-proven

Combined high-pressure valve and regulator (350 to 4.5 kgf/cm², 27 V DC, 1.9 kg) for spacecraft gas line control.

1 12
TRL 9 · Flight-proven

Thin-film strain-gauge pressure sensor for rocket/space systems (0–60 MPa range, 0.25% error, 0.15 kg, -196 to +50 °C, high vibration/shock resistance).

1 11

It is made according to "Regulation 98". Version: piezoresistive sensor with a protective metal membrane having flexible, numbered outputs.

1 5

Exception: the strain gage sensor can be supplied with a shock absorber at the request of the consumer. Type of protection - “Sealed enclosure”.

1 5

It is made according to "Regulation 98". Execution: the strain gage sensor at the request of the consumer is made with a screw fitting having a thread M12x1.25 or M18x1.5. Type of explosion protection - ”Sealed enclosure”.

1 5

Version: string converter (SC) and amplifier (A) connected by an integral cable jumper 0.5 m long. Cable jumper sheath TKR tube or steel 12X18H10T (depending on order). Explosion protection type - “Tight sheath”, cable jumper - “Intact cable network” or “Tight sheath” (depending on order).

1 5

Version: strain gauge sensor with cable jumper. At the request of the customer (in the absence of temperature control of the sensor on the product) it is manufactured with a heat-receiving sleeve. The type of explosion protection of the sensor is “Tight sheath”, cable jumper - “Intact cable network”

1 5

Version: thin-film strain gauge sensor with cable jumper. At the request of the customer (in the absence of temperature control of the sensor on the product) it is manufactured with a heat-receiving sleeve. The type of explosion protection of the sensor is “Tight sheath”, cable jumper - “Intact cabl

1 5

Propellant - hydrazine. The unit consists of 2 pressure stabilizers, 6 small-size solenoid valves that supply propellant to the thruster, and two pressure transducers to monitor propellant pressure. Thermal mode of the unit is ensured by 4 heaters (2 main and 2 redundant), a radiator, and a set of M

1 6

It is made according to "Regulation 98". Version: strain gauge sensor. The original structural unit and the use of special assembly methods allow you to shift the start of measurement to the level required by the customer. The sensor has a sealed design. Type of protection - “Sealed enclosure”.

1 5

It is made according to "Regulation 98". Exception: potentiometric transducer. The connection between the measurement object and the transducer is carried out using a rope.

1 5

The Software Complex consists of three modules. The Complex is designed for converting digital geodata from standard raster formats into a unified light tile format for data presentation, as well as for monitoring the results of re-conversion, on-line visualization and managing the total amount of d

1

The Program complex is intended for operational visualization of various geospatial information in near real time, as well as for solving a number of basic computing tasks based on it.

1 1

PMA is intended for propellant supply to stationary plasma thrusters. It provides an outlet flow rate of not less than 35 mg/s. Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procured parts and components (6 months

1 10
TRL 6 · Prototype

Electrothermal propulsion unit for CubeSat-class spacecraft (1.3 kg, 3–10 mN, 25–30 m/s ΔV for 5 kg spacecraft).

1 18
TRL 9 · Flight-proven

1-DOF electromechanical thruster pointing drive (±10.5°, 20 N·m, 7.3 kg, 520×390×300 mm) with 15-year life. Flight proven.

1 15
TRL 9 · Flight-proven

Explosion-proof hydraulic pumping station (50–400 kgf/cm², up to 35.5 kW, +5 to +35 °C, oil MGE-10A) for closed-loop spacecraft hydraulic systems.

1 14
TRL 9 · Flight-proven

Flight-proven pyrotechnic hold-down and separation lock (8500 kg clamping, 0.37 kg, 2 A actuation) with Glonass heritage.

1 10
TRL 9 · Flight-proven

Q-band band-pass filter for antenna feed system paths (SWR ≤1.15, ≤0.25 dB insertion loss).

1 4

ERS small-size multiband SAR, intended for operation aboard aircraft of different types. Mathematical, algorithmic and software.

1 4

PMT-187 has bialkali photocathode and 15-cascade secondary-electronic amplifier with mesh dynodes. The input window is made of boron-silicate UV glass, the first dynode is of “proximity” type.

1 10

Glavkosmos product — Radiation Hard Photomultiplier of High Immunity to Magnetic Fields 1. Details on request.

1 10

2/3" Vidicon LI501-1MK target is based on CdSe. Vidicon has magnetic focusing and electrostatic deflection.

1 10
TRL 9 · Flight-proven

Flight-proven passive radiation refrigerator (78 K, ≤350 mW, 830–36,000 km orbits) for spacecraft radiation receiver cooling. Heritage: Meteor-M, Electro-L.

1 12

As a result, the customer receives a specialized software and hardware VLSI SoC. VLSI may be the only solution that meets the requirements for use in radiation-resistant equipment of critical use.

1 4
TRL 9 · Flight-proven

Flight-proven COSPAS-SARSAT relay antenna set (402–406 MHz / 1544 MHz, 0–64° coverage, 5 kg) for Meteor-M spacecraft.

1 11

Modification of the RD120 liquid rocket engine with afterburning of oxidizing gas for the upper stages. Fuel: oxygen + kerosene. A number of new technologies are widely used in engine design. The basic engine RD-120 was developed in 1976-1985. The first launch of the Zenit launch vehicle with the RD

1 8

Liquid rocket engine with afterburning of oxidizing gas. Fuel: oxygen + kerosene. The most powerful liquid rocket engine in the world. More than 1000 fire tests were carried out with a total operating time of more than 110,000 s. During fire tests, engine performance was demonstrated in a wide range

1 8

Liquid rocket engine with afterburning of oxidizing gas. Fuel: oxygen + kerosene. Winner of the competition for the development and supply of the engine for the first stage for the PH of the Atlas family of the American company ULA. More than 260 tests were carried out with a total operating time of

1 8

Liquid rocket engine with afterburning of oxidizing gas. Fuel: oxygen + kerosene. The engine has the widest range of thrust regulation from 105-30%.

1 8

Modification of the RD120 liquid-propellant rocket engine with afterburning of oxidizing gas for the first stages. Fuel: oxygen + kerosene. A number of new technologies are widely used in engine design. The development of the RD182 engine is a terrestrial modification of the RD120MS with a short noz

1 8

Reaction wheels block contains four reaction wheels and provides work of three-axis orientation and stabilization system. Installation into CubeSat platforms provided. Reaction wheels dimensions: diameter 49 mm, width 12 mm, moment of inertia 150 g*cm2.

1 7
TRL 9 · Flight-proven

70 Ah / 28.8 V sealed rechargeable battery for space ground infrastructure power supply, 15-year service life.

1 13
TRL 9 · Flight-proven

90 Ah / 28.8 V sealed spacecraft rechargeable battery, 12,500 charge cycles, 2-year guaranteed service life.

1 15

Glavkosmos product — Rechargeable Battery for Power Supply of Spacecraft and Ground Infrastructure. Details on request.

1 9
TRL 9 · Flight-proven

Flight-proven Ka-band triple reflector assembly (3 × Ø1300 mm, ≤0.3 mm rms surface, 35 kg, metal-reflective coating) on 2900×2030 mm boom.

1 13

Two-degree-of-freedom electromechanical device for transferring the reflector boom from the transportation to the operational position and for antenna reflector pointing after its deployment.

1 10

Electromechanical device based on linear drives, which is designed to adjust reflective surface profile of the large reflector.

1 10
TRL 9 · Flight-proven

Flight-proven C-band contour reflector (Ø1800 mm, ≤0.5 mm rms surface, 9 kg) on 1830×790 mm boom for planimetric beam antennas.

1 12
TRL 7 · Demonstrated

Ku-band contour reflector (3500×2000 mm, ≤0.4 mm rms surface, 2.5 kg/m², 3850×1650 mm boom) for large planimetric beam antenna systems.

1 12

Two-degree-of-freedom electromechanical device for transferring the reflector boom from the transportation to the operational position and for antenna reflector pointing after its deployment.

1 10

Monoblock equipment for regulation and monitorung of the spacecraft’s power supply system. It is possible to change the design of the monoblock to increase power up to 10 kW by layout of internal submodules. It is planned to operate as part of a spacecraft for fundamental scientific space research.

1 9
TRL 9 · Flight-proven

Shock-free electromechanical release device (6 kg rod load, 0.08 kg, 41×41.5×41 mm, 75 actuations, flight-proven 2019).

1 12
TRL 9 · Flight-proven

Shock-free electromechanical release device (4 kg rod load, 0.05 kg, Ø38×41.7 mm, 50 actuations, flight-proven 2019–2020).

1 12
TRL 9 · Flight-proven

Linear electromechanical mast for umbrella-type reflector deployment (12 kg, 4100 mm length, 0.1 mm precision, 50 cycles).

1 14

Compact four-reflector "Pyramid" retroreflector for onboard calibration on the Condor-FKA satellite.

1 4

Interference-coated angle-reflector panel for laser ranging on the Luna-Globe lander/orbiter.

1 4

Seven-reflector retroreflector array for precision laser ranging of the ESA Sentinel-3 spacecraft.

1 5

36-reflector ring panel for metrological control and calibration of the GLONASS-K2 navigation constellation.

1 5

The receiving single-mirror antenna system includes an antenna with a reflector of 2.5 m with an S-band irradiating system, a slewing ring with electromechanical drives. The structure includes a low-noise input structure of the S-band.

1 7
TRL 9 · Flight-proven

SDR-based training ground station (136–438 MHz, 9600 bps, FSK, 2 fixed antennas, receives 50+ satellites including weather satellites).

1 11

Satellite laser ranging and velocity measurement system of spacecraft. It defines the distance considering the delay of reflected laser beam. Velocity measurement is carried out by means of doppler frequency at optical carrier. Receiving of 3D object image or its part.

1 6

Satellite multiband imaging system consist of two identical multispectral camera devices made in the form of separate structural units.

1 9

Assembled, verified and fully tested by the manufacturer satellite platform CubeSat 1U. Payload integration is possible before tests.

1 10

Assembled, verified and fully tested by the manufacturer satellite platform CubeSat 3U. Payload integration is possible before tests.

1 10

Assembled, verified and fully tested by the manufacturer satellite platform CubeSat 3U. Payload integration is possible before tests.

1 10

Assembled, verified and fully tested by the manufacturer satellite platform CubeSat 6U. Payload integration is possible before tests.

1 10

Screen-vacuum thermal insulation (SVTI) is one of the most common and reliable means of passive thermal control in the system for ensuring the thermal regime of a spacecraft. The use of SVTI provides the opportunity to significantly reduce the heat transfer rate of the structural elements and equipm

1

Version: monoblock, including a primary inductive converter and a gain unit. The sensor is tight. Permissible leakage is not more than 1.33 · 10-8 W (1 · 10-4 l · μm Hg / s). Type of protection - “Sealed enclosure”.

1 5

Version: forced-cooling piezoelectric sensor, consisting of a sensor installed in the housing and a flexible cable. Type of protection - “Intrinsically safe electrical circuit” - is provided by an intermediate converter.

1 5

Version: piezoelectric sensor, consisting of a sensor installed in the housing, and a flexible cable. Type of protection - “Intrinsically safe electrical circuit” - is provided by an intermediate converter.

1 5
TRL 9 · Flight-proven

Flight-proven spacecraft separation clamp band (9174 kg interface load, 0.5 kg) with heritage on Express, Yamal, KazSat, Loutch spacecraft.

1 11
TRL 9 · Flight-proven

Custom nanosatellite fixturing set for center-of-mass and inertia characteristic measurement equipment. Manufactured per nanosatellite design. Customizable.

1 4
TRL 7 · Demonstrated

Electromechanical telescopic spoke element for large transformable reflector deployment (>200 kg axial force, 27 V, 8 m stroke, 17-year life).

1 10

Uses Si photo-electric converters and has built-in electromagnetic coils. There is a 13 mm diameter aperture at the panel center with M2 mount holes for sun sensors or payloads.

1 10
TRL 9 · Flight-proven

Flight-proven Si side solar panel for CubeSats with built-in electromagnetic attitude coil, robust mechanical design.

1 19

The FAM signaling device includes the following blocks and nodes: optical block, power supply, control unit, PMT block, pulsed light source, flow limiter, set of mounting parts. Since 2009, at the Vostochny spaceport as part of the compressor station.

1 6

Bellows is a thin-wall metal pipe with corrugated (undulated) lateral surface. The bellows are manufactured of: alloy grade "36НХТЮ", beryllium copper grade "БрБ2", stainless steel 12Х18Н10Т, and brass grade "Л-80". Over 200 typical products are manufactured.

1
TRL 9 · Flight-proven

Flight-proven electromechanical deployment drive (25 N·m, 0.75 kg, 70×94×92 mm) for solar arrays and booms. Heritage: Amos-5, KazSat-3, Express.

1 13
TRL 9 · Flight-proven

Flight-proven electromechanical deployment drive (40 N·m, 0.6 kg, 75×90×70 mm) for solar arrays and booms. Heritage: Express-AM, Spektr-R, Elektro-L.

1 12
TRL 9 · Flight-proven

Flight-proven electromechanical deployment drive (25 N·m, 0.76 kg, 70×94×92 mm) for solar arrays and booms. Heritage: Express-AM5/AM6, Yamal-401.

1 13
TRL 9 · Flight-proven

Flight-proven high-torque electromechanical deployment drive (60 N·m, 0.7 kg, 60×60×145 mm). Heritage: Loutch-5A, Loutch-5B, Loutch-5V.

1 12
TRL 6 · Prototype

Electromechanical deployment drive (35 N·m, 0.75 kg, 85×93×80 mm) for solar arrays and booms with low anti-torque (0.2 N·m).

1 13

Electromechanical rotary drive for deployment of large mechanical system elements. With an angular position sensor.

1 8

Component of the mirror antenna. The main function of mirror antennas with a feed of this type is forming a narrow field pattern and repointing the antenna within the specified servicing area if required.

1 5

Glavkosmos product — Single-part and Small-scale Production of Ceramic Modules. Details on request.

1 3

Glavkosmos product — Single-part and Small-scale Production of Interconnection Ceramic Printed Circuit Boards. Details on request.

1 3

Precise and reliable gyroscopic device for measuring the angular coordinates of boreholes, including horizontal drilling, on the basis of fiber-optic gyroscopes and micromechanical accelerometers, which does not require the lifting of drill pipes and preinsertion in the borehole.

1 4

Determination of current coordinates, ground speed and course of traffic with help of space navigation systems(SNS) GLONASS and GPS , solution of service tasks, angle calculation , remembering of individual points and traffic routs, display current location on the map.

1 6

The small-size block for measuring the angular velocity is designed to measure the integrals of the absolute angular velocity vector projections of the spacecraft when operating in the orbital section of the spacecraft as part of the spacecraft control system. The instrument is designed as a free-fo

1 9

An upgraded version for KIND34-040. The small-size device for measuring the angular velocity is designed to measure the integrals of the absolute angular velocity vector projections of the spacecraft when operating in the orbital section of the spacecraft as part of the spacecraft control system. Th

1 9
TRL 9 · Flight-proven

Flight-proven SADM (5.3 kg, 280 A power transfer, 25 power circuits, 140,000-hr life). Heritage: Express-AM5, Express-AM6.

1 16
TRL 9 · Flight-proven

Flight-proven high-accuracy SADM (13.2 kg, 84 A, 0.083° error, 100,000-hr life) for large spacecraft. Customizable.

1 17
TRL 9 · Flight-proven

Flight-proven large SADM (22.7 kg, 420 A, 12 power circuits, 71,000-hr life) for GLONASS-M spacecraft.

1 16
TRL 9 · Flight-proven

Flight-proven compact SADM (4.3 kg, 90 A, 18 power circuits, 150,000-hr life) with extensive GEO heritage: Amos-5, Express, KazSat, Loutch.

1 16
TRL 9 · Flight-proven

Flight-proven high-accuracy SADM (4.5 kg, 70 A, 0.083° error, 100,000-hr life) for GLONASS-K spacecraft.

1 16
TRL 9 · Flight-proven

Flight-proven SADM (4.6 kg, 220 A, 8 power circuits, 98,000-hr life) with fast 0–24 deg/min rotation capability.

1 16
TRL 9 · Flight-proven

Deployable solar array wings (10–44 m², up to 25 kW) for all spacecraft types; flight-proven on Amos-5, Express-AM, Yamal, Elektro-L, Spektr-R and more.

1 13

The solar cell battery for CubeSat type spacecraft. Solar cell battery is the main element of power supply system, as well as a component part of a measurement and motion control complex satellite system.

1 2
TRL 9 · Flight-proven

Triple-junction GaInP2/GaAs/Ge solar cell for spacecraft power systems, 28.5% efficiency, flight-proven.

1 12
TRL 9 · Flight-proven

Solar panel deployment test stand (491 kg, 6145×2847×2847 mm) providing weight relief and opening-out testing of small spacecraft solar panels.

1 11
TRL 9 · Flight-proven

Flight-proven solar panel hold-down lock (2500 kg clamping, 0.8 kg) with extensive GEO/LEO heritage including Express, Yamal, Glonass.

1 12
TRL 9 · Flight-proven

Automated solar panel weightlessness testing system (12 suspension points, up to 80 kg each, 17 m longitudinal travel, 5 m transverse/vertical, <10% gravity compensation energy).

1 12
TRL 9 · Flight-proven

Ultra-lightweight (40 g) flight-proven solenoid valve (0.6 mm, 3.43 MPa, 500,000 cycles) for liquid/gas propellant flow control.

1 14
TRL 9 · Flight-proven

Ultra-lightweight (40 g) flight-proven solenoid valve (0.7 mm, 3.43 MPa, 500,000 cycles) for liquid/gas propellant flow control.

1 14
TRL 9 · Flight-proven

Flight-proven solenoid valve (2.8 mm, 3.0 MPa, 30,000 cycles, 180 g) for high-flow liquid and gaseous propellant control.

1 14
TRL 9 · Flight-proven

Flight-proven solenoid valve (2.2 mm, 2.94 MPa, 60,000 cycles, 180 g) for high-flow propellant control.

1 14
TRL 9 · Flight-proven

Flight-proven solenoid valve (1.8 mm, 2.94 MPa, 310,000 cycles, 180 g) for propellant flow control.

1 14

Platform for small spacecraft weighing up to 180 kg. Height of operation on different types of orbits – from low circular to geostationary. The ICA platform is divided into several independent modules. Each module separately is a subsystem of the platform and is a functionally and structurally separ

1 7
TRL 9 · Flight-proven

Small-satellite bus (up to ~70 kg) for technological, scientific and educational missions in low circular orbit.

1 17

Platform for small spacecraft weighing up to 700 kg. Height of operation on different types of orbits – from low circular to geostationary. The ICA platform is divided into several independent modules. Each module separately is a subsystem of the platform and is a functionally and structurally separ

1 9

On-board digital television system with up to 8 monoblock cameras and an onboard data recording/processing unit.

1 13

High-precision orientation and stabilization system for medium-orbit spacecraft with moments of inertia from 100 to 5000 kg·m². Made on the radiation-resistant element base of Russian rocket and space industry production

1 12

Mechanical device that consists of locks, spring-loaded pushrods, clamp-band with explosive pins, separation connectors, separation sensors.

1 7
TRL 9 · Flight-proven

Special LV transport vehicle (up to 120 km/h, 15000 kg, up to 20 m length, variable geometry) for heavy launch vehicle components.

1 11
TRL 6 · Prototype

PMT-176 spectrometric PMT (300–850 nm, 40 mm cathode Ø, S20 multialkali, 130 µA/lm, 1×10⁵ gain, 12-dynode). For gamma detection and nuclear physics.

1 19
TRL 6 · Prototype

PMT-183 spectrometric PMT (300–850 nm, 72 mm cathode Ø, S20 multialkali, 100 µA/lm, 8 ns rise time, venetian-blind 12-dynode). For gamma detection.

1 19
TRL 6 · Prototype

PMT-143-1 spectrometric PMT for fast processes (300–650 nm, 40 mm cathode Ø, SbKCs, ≥40 µA/lm, ≤3 ns rise time, 12-dynode).

1 19

Passive low-orbit glass retroreflector satellite for sub-millimeter precision satellite laser ranging and geodynamics research.

1 4

Passive HF power splitter for signal distribution in Ka-band flight communication equipment.

1 7

Passive HF power splitter for signal distribution in Ka-band flight communication equipment.

1 7
TRL 8 · Qualified

Autonomous star tracker for GEO (0.8 kg, 5 W, 1.5 arcsec cross-boresight at 22 Hz) with 7+ years prototype heritage.

1 17
TRL 8 · Qualified

Autonomous star tracker for LEO up to 1200 km (0.5 kg, 5 W, 1.5 arcsec cross-boresight at 22 Hz) with 7+ years prototype heritage.

1 17
TRL 8 · Qualified

Star tracker test simulator (wireless HDMI display mounted to star tracker blind, 5 V, 220 V wireless interface). Works only with Autonomous Measurement System.

1 10

Propellant - hydrazine. The unit consists of two modified thermocatalytic thrusters: 1 – main, and 1 – redundant. Thermal mode of the unit is ensured by 4 heaters (2 main and 2 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 4 temperature sensors. Manufacturing le

1 3

Propellant - hydrazine. The unit consists of two thermocatalytic thrusters: 1 – main, and 1 – redundant. Thermal mode of the unit is ensured by 4 heaters (2 main and 2 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 4 temperature sensors. Manufacturing lead time i

1 3

Thruster with a discharge power of up to 25 kW. Propellant - xenon. Development status – engineering model. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and eight external magnetic coils. Outside diameter of the accelerating channel is 230 mm

1 10

Thruster with a discharge power of up to 5 kW. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system of armored type with magnetic screens. Outside diameter of the accelerating channel is 140 mm. Mean diameter of the accelerating channel is 120 mm. Manu

1 10

Thruster with a discharge power of up to 6 kW. Propellant - xenon. Development status – laboratory model. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens. Outside diameter of the accelerating channel is 140 mm. Mean diameter of the accelerating

1 10

Thruster with a nominal discharge power of 1350 W. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and four external magnetic coils. Outside diameter of the accelerating channel is 100 mm. Mean diameter of the accelerating ch

1 10
TRL 9 · Flight-proven

Strain-gauge sensor for rapidly changing pressures in rocket/space systems (0–60 MPa, 0.8% error, 12 V, 0.22 kg, ±50 °C). Use with amplifiers LH-5514/LH-5515.

1 11

The accelerometer provides measurement of the apparent acceleration of ballistic and space equipment.

1 3

CubeSat 1U structure designed in accordance with CubeSat Design Specification rev.13 and supports modular satellite construction based on PC104 PCB stack with solar panels on the edges. For container launches there is a deployment system which consists of 2 separation springs and double separation s

1 7

CubeSat 3U structure designed in accordance with CubeSat Design Specification rev.13 and supports modular satellite construction based on PC104 PCB stack with solar panels on the edges. For container launches there is a deployment system which consists of 2 separation springs and double separation s

1 7

Sun Sensor is a two orthogonal axes digital sun sensor. It generates the directional cosines of the angles of the direction to the sun, thus, it doesn’t require any calibration. Besides, the sun sensor’s size and weight are very small, as is his power consumption which is ultra-low.

1 8
TRL 9 · Flight-proven

1000 W halogen sun simulator (1400 W/m² flux, Ø600 mm spot, 80,000 lx at 1.5 m, 12° beam, 220 V) for ADCS solar sensor testing.

1 13
TRL 9 · Flight-proven

Full-rotation 2-axis antenna mount for mirrors up to 5 m Ø (±270° azimuth, 0–180° elevation, 16°/s max speed, ≤800 kg load). Customizable.

1 12
TRL 9 · Flight-proven

Full-rotation 3-axis antenna mount for mirrors up to 6 m Ø (±270° az, 0–180° el, ±14° tilt, ≤1500 kg load). Customizable.

1 14

Operation princicple is based on the use of two independent high-speed channels of the tested product's surface illumination - the object channel (CO) and the background channel (CF).

1 6

Spacecraft are mounted on LV using quick-disconnect devices (locks, pyro-bolts, etc.) that release the spacecraft from the mount after the end of the last stage engine. Remaining free, the spacecraft can hit the detached part. To prevent this, the spacecraft separation system includes exciters (push

1
TRL 9 · Flight-proven

Spacecraft processing facility monitoring system (16 IP cameras, 48 TB archive, oxygen/propellant/temperature sensors, 18-month delivery). Customizable.

1 11

Temperature-controlled honeycomb panels with aluminium face sheets, fixed or attachable heat transfer tubes or fluid loops. Off-the-shelf efficient solutions include standard series of honeycomb fillers and face sheets, filling blocks; possibility of installing heat transfer tubes or fluid loop tube

1 5
TRL 9 · Flight-proven

Aerodynamic table for frictionless spacecraft mockup movement (5000×6000×3000 mm, 1860×2480 mm active area, 10 kg air-bearing load, 20 kW air pressure). Customizable.

1 13
TRL 9 · Flight-proven

CubeSat ADCS algorithm test stand (1700×17000×1775 mm, 250 kg magnetic stand, ≤2 kW) for control algorithm testing and student training. Customizable.

1 10

The mechanism is used in the testbed for testing antenna radio engineering performance in the ground conditions. Development of space version on the base of this solution is available.

1 9

Constructor for assembling nanosatellites from 1U to 12U of the CubeSat form-factor. Dimensions of modules for assembling 100х100х100 mm. Determination of position in space using the optical sensor, GPS/GNSS. Management of M-frames and gyrodyne The stage of manufacturing prototypes and conducting au

1 10

Nonablative thermal-protection silica-fiber-reinforced materials for coating the reusable spacecraft (TZMK-10(М) and TZMK-25(М), as well as radio engineering-purpose articles (TZMK-14М).

1 5

Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid valves that supply propellant to the thruster, and a pressure signaling indicator that monitors the fact that the thruster

1 10

Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid valves that supply propellant to the thruster, and a pressure signaling indicator that monitors the fact that the thruster

1 9

Version: thermoelectric converter (TC) consists of a sensitive element placed in the housing, a cable jumper and a connector. The sensitive element is based on a thermocouple cable with mineral insulation TU 16-505.757.

1 5

Consists of two units: M-70 Stationary Plasma Thruster and Xenon Flow Controller Unit (XFC Unit). Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procured parts and components (6 months).

1 10

TCM is a metal structure, which consists of a basement and a rotary frame. Hydraulic and electric equipment for the frame lifting / lowering is placed inside the basement. Electric cables run along the rotary frame. On top of the frame a couplers-removing mechanism is placed.

1
TRL 9 · Flight-proven

Automated weightlessness testing system for transformable reflectors and spacecraft equipment (36 suspension points, up to 10 kg each, 12 m travel in any direction, 1 m/min).

1 11
TRL 9 · Flight-proven

Flight-proven transition/adapter compartments for Soyuz (Ø3715/4110 mm) and Zenit (Ø4100 mm) launch vehicles (345–465 kg) for spacecraft-LV interface.

1 7

The eqiupment structually consists of: - Transport Unit tow-truck ; - Semi-trailer; - Special tank-container.

1 3

The station includes an antenna system with a reflector of 7.2 m Ku-band. The design of the reflector is collapsible. The structure includes an antenna on a folding slewing ring, a thermal container with a guidance system and channel-forming equipment.

1 9

Transportable navigation equipment 14Ц821 is designed to be used in equipment of motor-vehicles and armored machinery with the aim of solution of special coordinate-timing tasks.

1 6

Contains:Temperature control module, ventilation module, control module and power supply module of 2 modern diesel power generators.

1 4

The Transporter-Erector consist of a rigid metal frame, mounted on special railway carriages; a boom with the supports and special devices for ILV placing and transportation, assembled on the fame; hydraulic cylinders for boom erection into upright position and provision of ILV placing on launch pad

1 4

Assembled on Transporter-Erector frame pipe connector unit with mating device, providing mating with pipe connectors of Launch Complex, Assembling and Testing Facility, T.-E. depot.

1 4

Propellant - hydrazine. The unit consists of one modified thermocatalytic low thruster. Thermal mode of the unit is ensured by 2 heaters (1 main and 1 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 3 temperature sensors. Manufacturing lead time is given without t

1 3

Propellant - hydrazine. The unit consists of three modified thermocatalytic low thrusters. Thermal mode of the unit is ensured by 3 heaters (2 main and 1 redundant), a radiator, and a set of MLI. Unit temperature is monitored by means of 3 temperature sensors. Manufacturing lead time is given withou

1 3
TRL 9 · Flight-proven

Dual-channel strain-gauge weighing platform (2–10000 kg, ±0.1–6 kg error, 8 sensors per channel) for static weighing of propellant containers and liquid fuel charges.

1 11
TRL 6 · Prototype

2-DOF antenna pointing device (±85° per axis, 10 N·m, 7 kg, 370×370×250 mm) for pointing to mobile and immobile users.

1 15
TRL 9 · Flight-proven

Flight-proven 2-DOF antenna pointing device (±11.5°, 70 N·m, 21 kg, 855×725×233 mm) with 5-year GEO life.

1 14
TRL 9 · Flight-proven

Flight-proven 2-DOF antenna pointing device (±11.5°, 50 N·m, 13 kg, 565×500×210 mm) with 5-year life.

1 14
TRL 9 · Flight-proven

Flight-proven 2-DOF antenna pointing device (±10.5°, 50 N·m, 8.4 kg, 442×362×164 mm) with 10-year life.

1 14

Antenna deployment occurs by burning the filament. The device for burning the filament is duplicated. Telemetry monitoring of antenna deployment is performed.

1 8
TRL 9 · Flight-proven

Flight-proven UHF nanosatellite TT&C transceiver (43 g, 87×93×13 mm, 9600 bps, 1 W output, CAN2.0B, PC104) with SiriusSat-1/2 heritage.

1 17

Ultra-black coatings with reflection of non-informational radiation in the spectral range of 0.42-2.5 microns no more than 0.5 – 1.0 % with an active lifetime of 15 years.

1 5
TRL 9 · Flight-proven

High/expert-class diagnostic ultrasound scanner (21.5-inch Full HD, 4 probe ports, Color/Power/Pulse Wave Doppler, 3D Freehand, 512 GB SSD, 6 USB). 5-year life.

1 13
TRL 9 · Flight-proven

Expert-class diagnostic ultrasound scanner with single-crystal probe support (21.5-inch Full HD, 4 probe ports, S-Harmonic, optional Cardiac/CW Doppler). 5-year life.

1 13
TRL 9 · Flight-proven

Expert+ class diagnostic ultrasound scanner (21.5-inch Full HD, single-crystal probes, Elastoscan elastography option, optional Cardiac/CW Doppler). 5-year life.

1 13
TRL 9 · Flight-proven

Portable expert-class ultrasound scanner (15-inch, 1+1 CW probe ports, 128 GB SSD, built-in battery, Needle Mate, EZ-Exam, single-crystal probes). 5-year life.

1 15

UM is a metal structure, which consists of a basement and a rotary frame (consisting of two frames of different shape). Hydraulic and electric equipment for the frame lifting / lowering is placed inside the basement. Different kind of lines run along the rotary frame. At the top of the frame coupler

1

The unified DC-DC conversion module is included in the set of unified modules for critical power management systems. The set of unified modules for critical power management systems is designed for use in guaranteed power systems for aircraft engines, electric drives for pumping oil, gas, chemical p

1 16

The unified power control and management module is included in the set of unified modules for critical power management systems. A set of unified modules for critical power management systems designed for use in guaranteed power systems for aircraft engines, electric drives pumping oil, gas, chemica

1 19

The Unit provides necessary flow rate, pressure and temperature set by the operator, in the circuit of the Product's liquid fluid temperature control system. Intelligent operation control system. Self-diagnostic system.

1 4

Equipment consists of: - container equipped with two motor-generators; - set of uninterruptible power supplies; - set of low-voltage packaged devices; - remote control and management system.

1 4

Platform for small spacecraft weighing up to 700 kg. Height of operation on different types of orbits – from low circular to geostationary. The ICA platform is divided into several independent modules. Each module separately is a subsystem of the platform and is a functionally and structurally separ

1 7

Platform for small spacecraft weighing up to 700 kg. Height of operation on different types of orbits – from low circular to geostationary. The ICA platform is divided into several independent modules. Each module separately is a subsystem of the platform and is a functionally and structurally separ

1 7
TRL 9 · Flight-proven

Modular small-spacecraft platform (140-210 kg) for all orbit types, flight-proven on the MKA-FKI "Zond-PP" and "Relek" missions.

1 12
TRL 9 · Flight-proven

Modular spacecraft platform (850-980 kg) for astrophysical and meteorological missions, flight-proven on Electro-L and Spectrum-R.

1 12

In accordance with the specification of the customer. On the basis of the basic upper stage "Fregat" a number of highly efficient booster blocks have been created. The use of additional fuel tanks and a dropable block of tanks (upper stage "Fregat-MT" and upper stage "Fregat-SB") at upper stage "Fre

1 8

DRT-LSN, together with ORTD-LSN, is intended for use in the equipment of base stations and subscriber terminals of the local navigation system. Separately, DRT-LSN VLSI can be used as a microcontroller for universal use. The microcircuit is intended for use as part of the subscriber module of the LA

1 10
TRL 8 · Qualified

CMOS 90 nm 16-bit 200 MSps pipeline ADC (Н18.64-2В, 2.5 V, 26.6×26.6×2.9 mm, 3 g, 85 dB SFDR, 75 dB SNR, -60 to +85 °C, built-in calibration) for radar/comms.

1 20

Silicon-germanium BiKMOS VLSI broadband quadrature demodulator is designed for use in radio paths of military and special equipment and provides:

1 12

Silicon-germanium BiCMOS VLSI frequency synthesizer based on direct digital conversion is designed to produce a stable high-frequency signal in the 600 MHz range with an ultra-low frequency tunning step, low phase noise and fast frequency tunning, as well as the possibility of frequency, phase and L

1 14

Two-chip low-power VLSI kit (VLSI 1 + VLSI 2) for multi-channel combined GLONASS/GPS navigation receivers.

1 12

The microcircuit of the "System in the case" type (SIC) is intended for use in civil navigation equipment. It receives and processes GNSS signals: GLONASS L1OF, L1OC; GPS C/A L1; GALILEO E1B, E1C; as well as SBAS L1, DCMS L1OC and solutions to the navigation problem.

1 10

Semi-order programmable VLSI central computers are designed to create on their basis a new generation of integrated flight control systems (IFCS) of manned and unmanned aerial vehicles using heterogeneous communication channels. VLSI provide the design based on these circuits of the required functio

1 7

Silicon-germanium BiKMOS VLSI broadband quadrature modulator is designed for use in radio paths of special equipment and provides:

1 11

Current and voltage regulator for spacecraft onboard equipment. Is designed to provide spacecraft with electricity. Converts 110-180 V DC to 28,5 V DC. Voltage converter with other input/output voltage values can be built based on this design.

1 8

Current and voltage regulator for spacecraft onboard equipment. Is designed to provide spacecraft with electricity. Converts 28,5 V DC to 120 V DC. Voltage converter with other input/output voltage values can be built based on this design.

1 8

The voltage converter for onboard equipment of the spacecraft. Provides stable high-precision AC power for a single-phase network of spacecraft onboard equipment. Features: - output voltage frequency 1000 Hz POS 80 RNM is an upgraded voltage converter. It is designed to replace POS 80 RN voltage con

1 7

Elements of antenna feed system and flight communication equipment paths of different frequency bands.

1 7
TRL 9 · Flight-proven

Strain-gauge weighing device UVR-200 (0.5–100 kg, ±0.02–0.15 kg error) for static weighing of propellant containers and liquid fuel charges.

1 10
TRL 9 · Flight-proven

Strain-gauge platform weighing device (0.25–600 kg, ±0.1–0.3 kg error) for static weighing of propellant containers and liquid fuel charges.

1 7
TRL 9 · Flight-proven

Dual-channel strain-gauge weighing device UVDR-1200 (2–600 kg, ±0.01–0.6 kg error) for static weighing of propellant containers and liquid fuel charges.

1 10

Welded steel diaphragm bellows are unique products consisting of annular diaphragms with desired pattern, connected in series between each other by welding on the outside and inside diameter.

1
TRL 9 · Flight-proven

Hydrazine propellant tank (8.4 dm³, ≤2.5 kg) for monopropellant spacecraft propulsion systems, flight-qualified.

1 13

Mirror-type X-band antenna for spacecraft data transmission and reception with polarization selection.

1 8

The X-band transmitter designed for the lunar spacecraft (Luna-25 lander and Luna-26 orbiter). Сertified for compatibility with ESA ground stations.

1 8
TRL 6 · Prototype

X-band CubeSat downlink transmitter (1 Gbps, 0.38 kg, 22 W, 2.5 W output, QPSK/8PSK/16APSK, LVDS). Customizable. 3-year life.

1 14

Propellant – xenon, nitrogen. The thruster components are: a thermal accumulating chamber with a heater and a nozzle installed on it, two small-size solenoid valves that supply propellant to the chamber, and MLI. The thruster also has electrical connectors and a mounting plate that joins the thruste

1 10
TRL 9 · Flight-proven

Flight-proven xenon feed unit regulating 1.5–17 mg/s at 1.75 ± 0.1 kgf/cm² for orbit control electric thrusters, 2.6 kg.

1 13
TRL 9 · Flight-proven

Flight-proven xenon feed unit regulating 4–15 mg/s at 2.6 ± 0.12 kgf/cm² for orbit control electric thrusters, 2.6 kg.

1 13

Consists of a flow regulator that regulates the total flow rate; anode and cathode restrictors that ensure the required distribution of the propellant flow rate. Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procu

1 2

Consists of a flow regulator that regulates the total flow rate; anode and cathode restrictors that ensure the required distribution of the propellant flow rate. Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procu

1 2

Consists of a flow regulator that regulates the total flow rate; anode and cathode restrictors that ensure the required distribution of the propellant flow rate. Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procu

1 2

Consists of a flow regulator that regulates the total flow rate; anode and cathode restrictors that ensure the required distribution of the propellant flow rate. Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procu

1 2

Consists of two xenon flow controllers. Propellant - xenon. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procured parts and components (6 months).

1 6
TRL 7 · Demonstrated

Compact star tracker for nano/microsatellites (193 g, 0.5 W, 5 arcsec accuracy, LEO) developed by SPUTNIX.

1 14

The functional purpose of VLSI is the coordinated filtering and compression of FM and LFM weak signals with a base of 4096 or more. The use of VLSI SF in devices for secondary processing of weak signals allows to increase the detection range of targets while maintaining high resolution and allows th

1 14

Launch Slots

1
Soyuz 2.1b/Fregat-M
LO Available
Soyuz 2.1b/Fregat-M
31 Dec 2027
Vostochny Cosmodrome, Siberia, Russian Federation
Log in to request

Reviews

No reviews yet — reviews come only from verified buyers after a completed request.

Write a review

0 / 2000
← All providers