Propulsion

AAC Clyde Space provides small satellite technologies and space-based data services, offering end-to-end solutions from satellite components to data analytics for various applications.

AAC Clyde Space

AAC Clyde Space PM200 Bi-Propellant Propulsion Module

Bi-propellant propulsion module (offered with Dawn Aerospace) for 3-6U CubeSats, delivering over 230 m/s delta-v using non-toxic nitrous oxide/propene propellant.

Nominal thrust	0.5 N
Specific impulse (vac)	> 285 s
Total impulse	> 850 N.s
Delta-v (4 kg satellite incl. PM200)	> 230 m/s
Minimum impulse bit	35 mN.s

price on requestdatasheet

Aerospace company supporting space exploration missions; partners with ISRO, Skyroot, Orbex, Bellatrix, and Latitude on lunar and Mars programmes.

AADYAH Aerospace

Thrust Vector Control (TVC) System

Thrust Vector Control systems for solid and hybrid motor launch vehicles using flex nozzle, engine gimbaling, or liquid injection — flight-tested, AS9100D certified.

TVC methods	Flex Nozzle, Engine Gimbaling, Liquid Injection (LITVC)
Vehicle types	Solid and hybrid motor launch vehicles
Integration	GNC system and flight avionics compatible
Quality standard	AS9100D certified

price on request

US startup developing TILE electrospray propulsion chips for nanosatellites — ultra-compact, modular electric propulsion scaled from CubeSats to larger platforms.

Major US propulsion company (now part of L3Harris); RL10, RS-25/SLS engines, satellite thrusters, and solid rocket motors; 75+ years heritage powering US launch vehicles.

Aerojet Rocketdyne (L3Harris)

AEPS Advanced Electric Propulsion System

12 kW Hall thruster developed with NASA Glenn and JPL; three units will provide primary propulsion for the lunar Gateway Power and Propulsion Element.

Power level	12 kW
Type	Hall effect electric propulsion thruster
Development partners	NASA Glenn Research Center, NASA Jet Propulsion Laboratory
Status	Development testing completed 2021; qualification testing started at NASA Glenn 2023
Application	Three thrusters as primary propulsion for the lunar Gateway Power and Propulsion Element

price on request

Aerojet Rocketdyne (L3Harris)

AMBR 556 N Dual Mode High Performance Rocket Engine

556 N (125 lbf) Advanced Materials Bipropellant Rocket dual mode high performance engine for deep space and GEO missions.

Thrust	556 N (125 lbf)
Type	Dual mode high performance rocket engine
Propellants	Hydrazine or MMH fuel with NTO oxidizer

price on request

Aerojet Rocketdyne (L3Harris)

Green Propulsion Systems (AF-M315E)

Non-hydrazine green propellant propulsion, including modular 1U to 8U CubeSat propulsion systems offering up to 750 m/s delta-v.

Propellant	AF-M315E green propellant (hydrazine alternative)
Performance	50 percent higher performance than a traditional hydrazine system
CubeSat module sizes	1U to 8U
Delta-v capability	Up to 750 m/s
Flight demonstration	NASA Green Propellant Infusion Mission (GPIM)

price on request

Aerojet Rocketdyne (L3Harris)

Hydrazine Monopropellant Rocket Engines

Hydrazine monopropellant engine family from 0.02 lbf to 700 lbf thrust, with more than 19,000 units delivered.

Thrust range	0.02 lbf to 700 lbf
Propellant	Hydrazine (catalytic decomposition)
Units delivered	More than 19,000
Applications	Planetary transit course corrections, orbital capture and insertion, landing, precision po

price on request

Aerojet Rocketdyne (L3Harris)

NEXT-C Ion Propulsion System

7 kW gridded ion propulsion system based on NASA Glenn technology, flown as a technology demonstration on NASA's DART mission.

Power level	7 kW
Type	Gridded ion propulsion system
Technology basis	NASA Glenn Research Center mission-proven technology
Flight heritage	NASA DART mission, launched 2021 (technology demonstration)

price on request

Aerojet Rocketdyne (L3Harris)

R-1E 110 N Bipropellant Rocket Engine

110 N (25 lbf) storable bipropellant rocket engine for in-space maneuvering and attitude control.

Thrust	110 N (25 lbf)
Type	Bipropellant rocket engine
Propellants	Hydrazine or MMH fuel with NTO oxidizer

price on request

Aerojet Rocketdyne (L3Harris)

R-42 890 N Bipropellant Rocket Engine

890 N (200 lbf) storable bipropellant rocket engine for orbit raising and in-space maneuvering.

Thrust	890 N (200 lbf)
Type	Bipropellant rocket engine
Propellants	Hydrazine or MMH fuel with NTO oxidizer

price on request

Aerojet Rocketdyne (L3Harris)

R-42DM 890 N Dual Mode High Performance Rocket Engine

890 N (200 lbf) dual mode high performance rocket engine for spacecraft orbit raising and maneuvering.

Thrust	890 N (200 lbf)
Type	Dual mode high performance rocket engine
Propellants	Hydrazine or MMH fuel with NTO oxidizer

price on request

Aerojet Rocketdyne (L3Harris)

R-4D-11 490 N Bipropellant Rocket Engine

490 N (110 lbf) bipropellant rocket engine from the R-4D family originally developed for the Apollo programme.

Thrust	490 N (110 lbf)
Type	Bipropellant rocket engine
Propellants	Hydrazine or MMH fuel with NTO oxidizer
Family	R-4D

price on request

Aerojet Rocketdyne (L3Harris)

R-4D-15 HiPAT 445 N High Performance Rocket Engine

445 N (100 lbf) high performance bipropellant apogee engine, available in dual mode configuration; the R-4D lineage is the world's most reliable apogee insertion engine.

Thrust	445 N (100 lbf)
Type	Bipropellant; high performance and dual mode high performance configurations
Propellants	Hydrazine or MMH fuel with NTO oxidizer
Flight record (R-4D family)	Over 390 apogee-insertion missions for GEO satellites, 100% success rate

price on request

Aerojet Rocketdyne (L3Harris)

R-6F 22 N Bipropellant Rocket Engine

22 N (5 lbf) storable bipropellant rocket engine for fine in-space maneuvering and attitude control.

Thrust	22 N (5 lbf)
Type	Bipropellant rocket engine
Propellants	Hydrazine or MMH fuel with NTO oxidizer

price on request

Aerojet Rocketdyne (L3Harris)

RL-10 Upper Stage Engine Family

Liquid hydrogen / liquid oxygen upper-stage engine family powering Atlas V, Delta IV Heavy, Vulcan Centaur and NASA SLS, in service for six decades.

Propellants	Fuel: liquid hydrogen; Oxidizer: liquid oxygen
RL10B-2 / RL10C-2-1 (Delta IV)	Thrust 24,750 lbf; weight 664 lbs; MR 5.88:1; Isp 465.5 s; length 86.5 in stowed / 163.5 i
RL10A-4-2 (Atlas V)	Thrust 22,300 lbf; weight 370 lbs; MR 5.5:1; Isp 451.0 s; length 90 in; nozzle diameter 46
RL10C-1 (Atlas V)	Thrust 22,890 lbf; weight 420 lbs; MR 5.5:1; Isp 449.7 s; length 86 in; nozzle diameter 57
RL10C-1-1 (Atlas V, Vulcan Centaur)	Thrust 23,825 lbf; weight 415 lbs; MR 5.5:1; Isp 453.8 s; length 96.7 in; nozzle diameter

price on request

Aerojet Rocketdyne (L3Harris)

RS-25 Rocket Engine — Space Launch System Core Stage Propulsion

Staged-combustion LH2/LOX core stage engine for NASA's Space Launch System, evolved from the Space Shuttle Main Engine.

Cycle	Staged combustion
Propellants	Fuel: liquid hydrogen; Oxidizer: liquid oxygen; mixture ratio (O/F) 6.0
Thrust at 109% power level	Vacuum 512,300 lb; sea level 418,000 lb
Chamber pressure	2,994 psia
Specific impulse at 109% power level	Vacuum 452 s; sea level 366 s

price on request

Aerojet Rocketdyne (L3Harris)

XR-5 Hall Thruster System

Flight-proven Hall effect thruster subsystem used on AEHF, Northrop Grumman GEOStar-3 and Mission Extension Vehicles, and Lockheed Martin LM2100 satellites.

Type	Hall effect thruster subsystem
Status	Flight proven, in service
Platforms	AEHF constellation, Northrop Grumman GEOStar-3 and Mission Extension Vehicles, Lockheed Ma

price on request

In-space chemical propulsion manufacturer designing, 3D printing, and hotfiring hydrazine and bipropellant thrusters and engines in-house.

Agile Space Industries

Zero Slosh Piston Tanks

The Zero Slosh Piston Tanks are designed to ensure over 99.75% propellant expulsion efficiency and prevent slosh during maneuvers, constructed with Aluminum and PTFE seals.

Expulsion Efficiency	over 99.75%
Construction Materials	Aluminum and PTFE seals
Manufacturing Time	under six months

price on request

Airbus Defence and Space designs and manufactures satellites, spacecraft equipment, and provides related services for telecommunications, navigation, Earth observation, and space exploration.

Airbus Defence and Space

PureLine Topaz/THORs Power Processing Unit

The PureLine Topaz/THORs is a compact, innovative, and flexible Power Processing Unit (PPU) designed for satellite electric propulsion, particularly for New Space applications.

Lifetime

10 years in LEO

price on requestdatasheet

Aliena develops and manufactures Hall thruster systems for small satellites, providing integrated propulsion solutions for various satellite classes from nanosatellites to medium satellites.

aliena

MESSE Magnetically Enhanced Small Satellite Engine

Compact 350 W high-thrust Hall thruster for 100-500 kg platforms: 13.5 mN, ~1100 s Isp, over 200 kNs total impulse.

System power	350 W (nominal)
Thrust	13.5 mN
Specific impulse	~1100 s
Total impulse	> 200 kNs
Propellant	Kr / Xe

price on request

aliena

MUSIC Electric Propulsion System

Multi-stage Hall thruster with three operating modes covering 0.1 to 3 mN of thrust and 200 to 1000 s Isp in 1.5U or 4U form factors, flown since 2022.

Type	Multi-stage Hall thruster, modular design
Self-ignition mode	1.5U form factor, < 20 W, up to 0.25 mN, up to 200 s, 1 kNs total impulse, 2 kg wet mass,
Hot mode	4U form factor, < 100 W, ~3 mN, ~1000 s, 15 kNs total impulse, 5 kg wet mass, microsatelli
Dual mode / fault-tolerant	4U form factor, < 100 W, 0.1 to 3 mN, 200 to 1000 s, 15 kNs total impulse, 5 kg wet mass,
Fuel	Xe / Kr gas

price on request

aliena

MUSIC Hollow Cathode

Flight-ready 1 A-class LaB6 hollow cathode for Hall thrusters from 70 to 350 W, 50 g in 3 x 4.5 cm.

Type	Heated, ceramic encapsulated
Emitter	Lanthanum hexaboride (LaB6)
Current	0.2 - 1.2 A
Ignition heating power	< 50 W
Flow rate (Xe)	0.05 - 0.16 mg/s

price on request

aliena

µCAT Propulsion System

The µCAT (Micro Cathode Arc Thruster) is a miniaturized electric propulsion system developed by Aliena, a Singapore-based space startup. Using a solid titanium propellant and requi

price on request

Apollo Fusion (Astra) designs and manufactures flight-proven electric propulsion systems for satellites and provides launch services, headquartered in Alameda, California.

Apollo Fusion (Astra)

Apollo Constellation Engine

ACE is a compact Hall-effect thruster propulsion system developed by Apollo Fusion (acquired by Astra in 2021) for smallsat and constellation electric propulsion, offering multi-pr

Thruster type	Hall-effect thruster
Propellant	Krypton, Xenon, or proprietary propellants (multi-propellant capable)
Input power	400 W (operable 280-600 W)
Thrust (Krypton)	~18 mN
Thrust (Xenon)	~25 mN

price on request

Apollo Fusion (Astra)

Apollo Constellation Engine (ACE) Ion Thruster

Apollo Fusion's ACE — a 200 W Hall-effect ion thruster for small satellites, providing cost-effective electric propulsion for constellation station-keeping and orbit transfers.

Type	Hall-effect ion thruster
Power	200 W
Thrust	~12 mN
Specific Impulse	~1,600 s
Propellant	Xenon

price on request

Applied Ion Systems develops and tests micro End Hall Thrusters for electric propulsion.

Applied Ion Systems

AIS-gPPT3-1C Series Integrated Propulsion Module

An open-source, ultra-low-cost micro pulsed plasma thruster module designed for PocketQubes and CubeSats, with confirmed flight heritage on orbit aboard a 1U CubeSat. Now retired.

Thruster Type	AIS-gPPT3-1C Micro Pulsed Plasma Thruster
Fuel	Teflon
Power Draw	500mW
Primary Capacitor Bank	0.136uF
Primary Bank Working Voltage	2kV

$2 500datasheet

Applied Ion Systems

AIS-SWAG1-PQ Sublimation Warm Gas Thruster

A PocketQube-class sublimation warm gas thruster using solid unpressurized Adamantane propellant, providing 120uN thrust for up to 7 hours of operation.

Type	Sublimation Warm Gas Thruster
Fuel	Solid Unpressurized Adamantane
Power	5W
Thrust	120uN
Operating Lifetime	7 hours

$4 500

Applied Ion Systems

AIS-SWAG1-QUAD

The AIS-SWAG1-QUAD is a Sublimation Warm Gas Thruster designed for CubeSats, offering 480uN of thrust and a total impulse of 12Ns, enabling significant orbital movement for small s

Type	Quad Sublimation Warm Gas Thruster
Fuel	Solid Unpressurized Adamantane
Power	20W
Thrust	480uN
Operating Lifetime	7 hours

$12 500

Applied Ion Systems

AIS-VAT0-DEMO Educational DIY Micro Vacuum Arc Thruster Kit

The first off-the-shelf DIY educational electric propulsion learning kit, allowing anyone to build and fire a fully operational micro vacuum arc thruster based on real flight-modul

Type	Micro Vacuum Arc Thruster Demo DIY Kit
Power	2.5W
Shot Lifetime (10^-2 Torr)	>300,000
Shot Lifetime (10^-6 Torr)	60,000
Rep Rate	Single Shot to 8Hz

$570datasheet

Applied Ion Systems

AIS-VAT1-DUO Dual Micro Vacuum Arc Thruster

A dual-module micro vacuum arc thruster cluster consisting of two parallel AIS-VAT1-PQ units, sized for CubeSats down to 1U or even 1/2U class satellites.

Type	Dual Micro Vacuum Arc Cluster
Power	5W or 10W Options
Min Thrust	8.4uN (1W)
Max Thrust (5W)	26uN
Max Thrust (10W)	52uN

$4 800

Applied Ion Systems

AIS-VAT1-PQ

A flight-qualified micro vacuum arc thruster (MVAT) using solid bismuth fuel, designed to provide propulsion for PocketQube and small CubeSat satellites.

Type	Micro Vacuum Arc Thruster
Power	2.5W or 5W Options
Thrust (Beginning of Life)	26uN
Thrust (End of Life)	<1uN
Shot Lifetime	40,000

$3 500

Applied Ion Systems

AIS-VAT1-PQ Micro Vacuum Arc Thruster

The smallest thruster in the AIS-VAT Series — an ultra-low-cost micro vacuum arc thruster sized for 1.5P PocketQubes up to 1U CubeSats, using solid Bismuth fuel for maximum thrust-

Type	Micro Vacuum Arc Thruster
Power	2.5W or 5W Options
Min Thrust	4.2uN (<1W)
Max Thrust (2.5W)	13uN
Max Thrust (5W)	26uN

$2 500

Applied Ion Systems

AIS-VAT1-QUAD Quad Micro Vacuum Arc Thruster

A quad-module micro vacuum arc thruster cluster consisting of four parallel AIS-VAT1-PQ units, providing up to 104uN thrust for CubeSats down to 1U class satellites.

Type	Quad Micro Vacuum Arc Cluster
Power	10W or 20W Options
Min Thrust	16.8uN (2W)
Max Thrust (10W)	52uN
Max Thrust (20W)	104uN

$6 500

Applied Ion Systems

AIS-VAT2 Vacuum Arc Thruster

The AIS-VAT2 is a next-generation vacuum arc thruster designed for CubeSats, offering propulsion at 20W or less and fitting within a 0.5U volume.

Type	Vacuum Arc Thruster
Power	20W
Thrust (Beginning of Life)	128uN (at 2Hz)
Thrust (End of Life)	32uN (at 2Hz)
Shot Lifetime	up to 300,000

price on request

Applied Ion Systems

AIS-VAT3 Vacuum Arc Thruster

The AIS-VAT3 is a 40W-class vacuum arc thruster (VAT) developed by Applied Ion Systems, scaled up from the VAT1-PQ design for use on larger CubeSats up to 6U-class. Development of

Type	High Power Vacuum Arc Thruster
Power	40W
Thrust	256uN (at 4Hz)
Thrust (End of Life)	64uN (at 4Hz)
Shot Lifetime	up to 300,000

price on request

ArianeGroup designs and manufactures space transport systems, including launchers and related technologies, for institutional, commercial, and industrial customers in civil and military sectors.

arianegroup

Prometheus Reusable Rocket Engine

ArianeGroup's Prometheus — Europe's first LOX/methane reusable rocket engine designed to reduce costs by a factor of 10 vs. Vulcain, targeting future reusable European launchers.

Propellants	LOX/Liquid Methane (LCH4)
Thrust	~100 kN
Cycle	Gas generator
Target Cost vs. Vulcain 2.1	10× cheaper
Manufacturing	Extensive 3D metal printing of components

price on request

Space technology startup developing solutions for orbital logistics and in-space operations.

US startup developing GEO satellite constellation for high-capacity broadband connectivity with advanced software-defined payload.

Astra Space designs and manufactures responsive mobile launch systems (Rocket 4.0) and flight-proven electric propulsion systems for satellites, headquartered in Alameda, California.

Astra Space

Astra Satellite Engine (ASE)

Flight-proven Hall-effect electric propulsion system for small satellites, operating on xenon or krypton with scalable multi-thruster configurations.

Propellant	Xenon (Xe) or Krypton (Kr)
Input power	400 W (single string)
Thrust (Xe)	~25 mN
Thrust (Kr)	~18 mN
Specific impulse (Xe)	~1,400 s

price on request

US aerospace startup developing lightweight aviation jet engines using novel manufacturing techniques to dramatically reduce cost and weight.

Astro Mechanica

Electric Jet Engine Propulsion for Suborbital Flight

Astro Mechanica's electric jet engine augmented rocket first stage — using turbine-driven air-breathing propulsion at low altitude to reduce propellant mass and improve launch econ

Concept	Electric jet augmented rocket first stage (air-breathing + chemical propulsion)
Advantage	Reduces LOx mass required in dense lower atmosphere
Operating Range	Ground level through transonic (Mach 0.8–1.2)
Funding	AFRL SBIR (US Air Force Research Laboratory)
Stage	Technology development / engine testing

price on request

Astro Mechanica

Lightweight Aviation Jet Engine

Astro Mechanica’s debut jet engine is a lightweight turbine designed for small aircraft, advanced air mobility platforms, and UAVs. Developed using novel manufacturing techni

Engine type	Turbojet / turbofan
Thrust class	TBD (in development)
Applications	Small aircraft, UAV, advanced air mobility
Manufacturing	Novel low-cost additive + subtractive
Status	Development / ground test

price on request

Advanced Technology Institute (ATI) is a Tokyo-based space engineering firm supporting satellite and launch vehicle development, manufacturing thermal vacuum chambers, and supplying space-grade components including propulsion systems, senso

ATI Space (Advanced Technology Institute)

Electric Propulsion Systems

ATI Space supplies a range of electric propulsion systems for small and CubeSat spacecraft, including nano pulsed plasma thrusters (PPT), Hall effect thrusters, ADN green propulsio

Types	PPT, Hall effect, ADN green, nanoFEEP
Applications	CubeSat, nanosatellite, microsatellite
Functions	Orbit raising, station keeping, deorbit
Propellant	Electric, ADN green, xenon

price on request

Finnish manufacturer of water-propellant resistojet thrusters and propellant-free plasma brake deorbiting tethers for small satellites, from CubeSats to SmallSats.

Aurora Propulsion Technologies

ARM-O (Aurora Resistojet Module for Orbit Control)

A modular water-propellant resistojet thruster module for satellite orbit control, ideal for collision avoidance and small orbital maneuvers on SmallSats, CubeSats and PicoSats.

Propellant	Water
Thrust-to-power ratio	Ten times more thrust to power need compared to FEEP
Specific impulse	Double the specific impulse compared to cold gas
Target platforms	SmallSats, CubeSats and PicoSats
IOD	2026

price on requestdatasheet

Aurora Propulsion Technologies

Aurora ARM Thruster System

Plug-and-play, ITAR-free resistojet propulsion modules for CubeSats and small satellites up to 300kg, providing attitude control, orbital maneuvering, and zero-debris-compliant end

Thrusters in Orbit	14
Space Heritage	4 Years
Supply Chain	European
Products launched	14 ARM thrusters, 3 Plasma Brake tethers
Launch scheduled	11 ARM thrusters, 2 Plasma Brake tethers

price on request

Aurora Propulsion Technologies

Aurora Resistojet Module for Orbit Control (ARM-O)

A modular water-propellant resistojet thruster module for satellite orbit control, designed for collision avoidance and small orbital maneuvers on SmallSats, CubeSats and PicoSats.

Thrust-to-power need	10x more than FEEP
Specific impulse	2x compared to cold gas
Propulsion safety	Safe and reliable propulsion
Flight heritage / IOD	IOD 2026
Applicable platforms	SmallSats, CubeSats, PicoSats

price on requestdatasheet

Aurora Propulsion Technologies

Multi-Modal Electric Propulsion Engine (MEPE)

5U dual-mode electric propulsion system combining Hall-effect thruster and resistojet modes with green propellant — orbital maneuvers up to 150 kg, flew as IOD in 2023.

Form Factor	5U
Propulsion Modes	Hall-effect thruster + resistojet
Propellant	Green (non-toxic)
Max Serviceable Satellite Mass	~150 kg
Flight Heritage	IOD launched 2023 (ORB-12 STRIDER)

price on requestdatasheet

Aurora Propulsion Technologies

Propulsion systems for maneuvers in space

Aurora Propulsion Technologies offers plug-and-play, ITAR-free, and zero-debris compliant propulsion systems for LEO architectures, designed for CubeSats and SmallSats.

Products launched	14 ARM thrusters
Products launched	3 Plasma Brake tethers
Launch scheduled	11 ARM thrusters
Launch scheduled	2 Plasma Brake tethers
Space Heritage	4 Years

price on request

Aurora Propulsion Technologies

Small Plasma Brake (APB-S)

Propellant-free deorbiting tether for CubeSats — fits TunaCan extra volume allocation, up to 400m tether, effective for satellites up to ~100kg on orbits up to 1000km.

Deorbit Mechanism	Propellant-free Coulomb drag microtether
Tether Length	Up to 400 m
Max Serviceable Satellite Mass	~100 kg
Effective Orbit Altitude	Up to 1000 km
Form Factor	TunaCan extra volume allocation

price on requestdatasheet

Indian in-space propulsion company developing electric and green chemical thrusters and orbital transfer vehicles for missions from nanosatellites to GEO platforms.

Bellatrix Aerospace

Arka Hall Effect Thruster Series

Family of Hall Effect Thrusters from 50 W to 5 kW for cubesats through large GEO platforms.

Arka 50 - Thrust	3 mN
Arka 50 - Power	50 W
Arka 50 - Specific impulse	860 s
Arka 100 - Thrust	7 mN
Arka 100 - Power	100 W

price on request

Bellatrix Aerospace

Fingernail Nanosatellite Propulsion Module

Compact one-piece plug-and-play propulsion system for nanosatellites, enabling collision avoidance and de-orbit.

Form factor	One-piece, coin-sized assembly
Manufacturing	Advanced nano fabrication, single-piece construction
Interface	Plug and play
Capabilities	Collision avoidance, de-orbiting
Target platform	Nanosatellites

price on request

Bellatrix Aerospace

Jal Microwave Plasma Thruster

Water-fuelled microwave plasma electric thruster with zero propellant cost, for GEO and high-power missions.

Thrust (Jal 5000)	300 mN
Power input	5000 W
Specific impulse	1050 s
Operational lifespan	>20,000 hours
Propellant	Water

price on request

Bellatrix Aerospace

Rudra Green Propulsion Thruster Series

Green monopropellant thruster family (1 N, 5 N, 100 N) offering a non-toxic alternative to hydrazine.

Rudra-1 - Thrust	1 N
Rudra-1 - Impulse bit	<50 mN·s
Rudra-1 - Vacuum Isp	235 s
Rudra-5 - Thrust	5 N
Rudra-5 - Impulse bit	<0.1 N·s

price on request

Bellatrix Aerospace

RUDRA Hall Effect Thruster

RUDRA is a Hall Effect Thruster (HET) developed by Bellatrix Aerospace of India for small satellite propulsion. It is designed for attitude control, orbit raising, and station-keep

price on request

US propulsion company in Burlington, VT; 39 chemical and 19 electric systems launched; chemical, electric, and hybrid thrusters with full mission assurance.

Benchmark Space Systems

Halcyon

Halcyon is Benchmark Space Systems' flagship non-toxic ('green') chemical propulsion product line, offering catalytic monopropellant and dual-mode bipropellant thrusters built arou

Thrust (Monopropellant HTP)	250 mN, 1 N, 5 N, 10 N
Thrust (Dual-Mode Bipropellant)	2 N, 10 N, 22 N
Specific impulse (Monopropellant)	150-170 s
Specific impulse (Bipropellant)	290-310 s
Propellant	High-Test Peroxide monopropellant; HTP + fuel injection bipropellant

price on requestdatasheet

Benchmark Space Systems

Peregrine Bipropellant Thruster System

Green bipropellant propulsion system for 6U to ESPA-class satellites. HTP + Alcohol, >270 s Isp, 100 mN–22 N thrust, ODPS pressurization.

Propellant	HTP (High-Test Peroxide) + Alcohol
Specific Impulse	> 270 s
Thrust Range	100 mN – 22 N
Minimum Impulse Bit	< 0.5 mN·s
Dry Mass	4.0 kg

price on request

Benchmark Space Systems

Starling Ardent

The Starling Ardent system is a resistojet thruster designed to maximize efficiency and double the specific impulse of typical gas systems.

Thrust Range	10 mN – 1 N
Specific Impulse	70 s (cold gas); 105–150 s (resistojet)
Minimum Impulse Bit	< 0.05 mN·s
Max Total Impulse	2 kN·s
Propellant	Non-toxic inert gas (ODPS™)

price on request

Developer of deployable solar arrays delivering scalable power for orbital data centers, space stations, and lunar operations.

Blue Orbit Space Systems is a German deep-tech startup based in Bremen that develops electric propulsion systems for small satellites and plasma-based solutions for industrial applications.

Blue Orbit Space Systems

Blue Orbit Water Resistojet

Water-propellant resistojet for LEO in two configurations: 270 g at 3.3-4.4 mN and 250 g at 27-30 mN, both around 103-108 s Isp.

Propellant	Water
Configuration 1 - mass	270 g
Configuration 1 - dimensions	55 x 33 x 122 mm
Configuration 1 - power	10 - 18 W (estimate)
Configuration 1 - thrust	3.3 - 4.4 mN (estimate)

price on requestdatasheet

Blue Orbit Space Systems

TRINIT-ION Gridded Ion Thruster

Argon/nitrogen gridded ion thruster of the TRINITY series: under 50 mN thrust, up to 2500 s Isp, total impulse below 2000 kN-s.

Propellant	Argon, Nitrogen
Mass (incl. thruster and cathode)	2.5 kg
Dimensions	90 x 85 x 115 mm
Nominal input power	800 - 1200 W
Operational power range	1500 W

price on requestdatasheet

Blue Orbit Space Systems

TRINITY ABE Air Breathing Thruster

Air-breathing electric thruster of the TRINITY series for VLEO operation at 180-250 km: under 20 mN thrust, up to 2000 s Isp.

Propellant	Argon, Nitrogen
Mass (incl. thruster and cathode)	2.5 kg
Dimensions	90 x 85 x 115 mm
Nominal input power	800 - 1200 W
Operational power range	1500 W

price on requestdatasheet

Blue Orbit Space Systems

TRINITY HET Hall Effect Thruster

Argon/nitrogen Hall effect thruster of the TRINITY series for small satellites: under 100 mN thrust, up to 1100 s Isp, LEO to GEO.

Propellant	Argon, Nitrogen
Mass (incl. thruster and cathode)	2.5 kg
Dimensions	90 x 85 x 115 mm
Nominal input power	800 - 1200 W
Operational power range	1500 W

price on requestdatasheet

Heavy-lift reusable launch — New Glenn; suborbital tourism & research — New Shepard.

Blue Origin

BE-4 Engine

High-thrust LOX/LNG rocket engine powering New Glenn and Vulcan Centaur, designed for high reusability.

Thrust (vacuum)	~2,400 kN per engine
Propellant	LOX / LNG (liquefied natural gas)
Cycle	Oxidizer-rich staged combustion
Reusability target	25+ flights per engine
Applications	New Glenn (×7 first stage); Vulcan Centaur (×2)

price on request

Blue Origin

New Shepard

Fully reusable suborbital launch system for crew and payloads, featuring a pressurized capsule and propulsively-landing booster.

Max altitude	>100 km (above Kármán line)
Crew capacity	6 passengers
Microgravity duration	~3 minutes
Booster engine	BE-3 (LH2 / LOX)
Booster thrust	489 kN

price on request

Swedish green propulsion pioneer; HPGP / LMP-103S thrusters using ADN propellant with 12% higher Isp than hydrazine; Bradford ENOVIA group.

Bradford Space

1 N GP Thruster

Green propellant thruster variant delivering 1 N thrust for low-toxicity attitude control and delta-V maneuvers.

Thrust	0.25-1 N
Propellant	LMP-103S (ADN-based, non-toxic)
Function	AOCS + ΔV

price on request

Bradford Space

1 N HPGP Thruster

Flight-proven HPGP monopropellant thruster delivering 0.25-1 N thrust, used for AOCS and delta-V on CubeSats to smallsats.

Thrust	0.25-1 N
Specific Impulse	204-231 s
Mass	0.39 kg
Pulse Count	60,000
Feed Pressure	5.5-22 bar

price on request

Bradford Space

100 mN HPGP Thruster

Low-toxicity ADN-based HPGP monopropellant thruster delivering 0.1 N thrust for AOCS and small delta-V maneuvers.

Thrust	0.1 N
Specific Impulse	≥190 s
Mass	0.04 kg
Pulse Count	2,000
Feed Pressure	2.3-4.5 bar

price on request

Bradford Space

200 N HPGP RCS Thruster

Reaction control system configuration of the 200 N HPGP monopropellant thruster for high-thrust attitude and orbit control.

Thrust	50-200 N
Specific Impulse	206-234 s
Mass	5.7 kg
Pulse Count	2,000
Feed Pressure	5.5-24 bar

price on request

Bradford Space

200 N HPGP Thruster

High-thrust HPGP monopropellant engine delivering 50-200 N for reaction control system (RCS) applications.

Thrust	50-200 N
Specific Impulse	206-234 s
Mass	5.7 kg
Pulse Count	2,000
Feed Pressure	5.5-24 bar

price on request

Bradford Space

22 N HPGP Thruster

High-endurance HPGP monopropellant thruster delivering 5.5-22 N thrust for AOCS and delta-V maneuvers on medium satellites.

Thrust	5.5-22 N
Specific Impulse	235-250 s
Mass	1.0 kg
Pulse Count	50,000
Feed Pressure	5.5-24 bar

price on request

Bradford Space

5 N HPGP Thruster

Mid-class HPGP monopropellant thruster delivering 1.4-5.5 N thrust for AOCS and delta-V on small and medium satellites.

Thrust	1.4-5.5 N
Specific Impulse	220-245 s
Mass	0.45 kg
Pulse Count	50,000
Feed Pressure	5.5-24 bar

price on request

Bradford Space

Bradford Miniaturised Pressure Transducer

Ultra-compact 180 g space-qualified pressure transducer, 3–320 bar range, ±0.3% FS accuracy, for small spacecraft propulsion systems.

Model	Miniaturised
Max Pressure Range	3–320 bar
Accuracy (BoL)	±0.3% FS
Accuracy (EoL)	±0.4% FS
Mass	180 g

price on requestdatasheet

Bradford Space

Bradford Standard Accuracy Pressure Transducer

Space-qualified pressure transducer, 1–310 bar range, ±0.3% FS BoL accuracy, 250 g, compatible with hydrazine, MON, MMH and other propellants.

Model	Standard
Max Pressure Range	1–310 bar
Accuracy (BoL)	±0.3% FS
Accuracy (EoL)	±0.4% FS
Mass	250 g

price on requestdatasheet

Bradford Space

HPGP 200N Thruster — High-Performance Green Propellant Propulsion

Bradford ECAPS (part of Bradford Space) is a Swedish space propulsion company developing High Performance Green Propellant (HPGP) thrusters using LMP-103S propellant — a non-toxic,

price on request

Bradford Space

HPGP High Performance Green Propellant Thruster

Bradford ECAPS (a subsidiary of Bradford Space) is a Swedish aerospace company and world leader in High Performance Green Propellant (HPGP) propulsion systems. Their thrusters use

price on request

Busek Co. Inc. designs, develops, and manufactures electric propulsion thrusters and related space hardware for military, government, and commercial satellites, with a focus on Hall, electrospray, RF

Busek Co.

BET-MAX Electrospray Thruster System

Multi-axis precision electrospray propulsion system (BET-300P thrusters) for ultra-precise attitude/orbital control down to 1U platforms.

Thruster module	BET-300P passively-fed electrospray thruster, 125 cm³
Thrusters per PPU	Up to 4
Thrust range	< 1 µN to 150 µN, sub-µN resolution
Impulse per module	> 100 N·s
Neutralizer	Carbon Nanotube Field Emission Cathode (CNTFEC), propellant-less

price on request

Busek Co.

BGT-X5

Busek's BGT-X5 is a 0.5N green monopropellant thruster system delivering 565 N-s of total impulse within a 1U CubeSat volume, using the stable ASCENT propellant as a hydrazine alte

Propellant	ASCENT
Thrust	500 mN nominal
Specific Impulse	220-225 s
Total Impulse	565 N-s
System Power	20W

price on requestdatasheet

Busek Co.

BHT-100

The BHT-100 is a compact, magnetically shielded Hall thruster designed for small spacecraft, offering high efficiency and a predicted lifetime of 10,000 hours or more.

Discharge Power	100 W
Voltage	200 VDC
Thrust	7 mN
Specific Impulse	1000 seconds
Propellants	Xenon, Iodine

price on requestdatasheet

Busek Co.

BHT-1500

The BHT-1500 is a 2kW-class Hall Effect thruster featuring an innovative center-mounted cathode, designed for efficient and high-performance propulsion using xenon, krypton, or iod

Nominal Discharge Power	1,500 W
Discharge Power Range	1,000-2,700 W
Nominal Thrust	101 mN (Xe)
Propellants	Xenon, Krypton, Iodine
Nominal Specific Impulse	1710 seconds

price on requestdatasheet

Busek Co.

BHT-200

The BHT-200 is a high-performance, mature Hall effect thruster with flight heritage, designed for spacecraft propulsion and capable of operating with various propellants including

Specific Impulse	1390 seconds
Demonstrated Impulse	74.88 kN⋅s
Predicted Total Impulse	>140 kN⋅s
Discharge Power	200 W
Voltage	250 VDC

price on requestdatasheet

Busek Co.

BHT-20K

The BHT-20K is Busek's highest power Hall thruster to date, designed for high-power space missions and capable of delivering 1 Newton of thrust.

Discharge Power	20,000 W
Voltage	450 VDC
Thrust	1006 mN
Propellants	Xenon, Krypton, Iodine
Specific Impulse	2515 seconds

price on requestdatasheet

Busek Co.

BHT-350

The BHT-350 is a Hall Effect thruster designed for high-volume production and scalability in new space applications, offering an economical propulsion solution for constellations a

Nominal Discharge Power	350W
Throttle Range	200W-600W
Nominal Thrust	17mN
Propellants	Xenon, Krypton, Iodine
Nominal Specific Impulse	1244s

price on requestdatasheet

Busek Co.

BHT-600

The BHT-600 is a high-performance, long-life Hall Effect thruster designed for small satellites, offering primary propulsion and attitude control with options for direct mount or 1

Nominal Discharge Power	600W
Discharge Power Range	300-800 W
Thrust	39 mN (Xe)
Propellants	Xenon, Krypton, Iodine
Specific Impulse	Up to 1500 seconds

price on requestdatasheet

Busek Co.

BHT-6000

The BHT-6000 is a high-performance Hall effect thruster optimized for mid-to-high power applications, capable of operating in both high thrust and high impulse modes.

Nominal Discharge Power (High Thrust Mode)	5,000 W
Voltage (High Thrust Mode)	300 V
Thrust (High Thrust Mode)	320 mN
Specific Impulse (High Thrust Mode)	2,029 s
Nominal Discharge Power (High Impulse Mode)	6,000 W

price on requestdatasheet

Busek Co.

BIT-3 RF Ion Thruster

Compact iodine-fueled gridded RF ion thruster; flown on NASA SLS deep-space CubeSat missions.

System Power	56-75 W
Thrust	Up to 1.1 mN
Specific Impulse	Up to 2150 s
System Dry Mass	1.40 kg (with gimbal)
Delta-V	Up to 2.39 km/s (14 kg CubeSat)

price on request

Capsule Corporation is an Italian space propulsion startup developing WaterCube, a water-based propulsion system for CubeSats and small satellites, enabling cost-effective orbital maneuvers with a green, unpressurized propellant.

Capsule Corporation

WaterCube Propulsion Unit

The WaterCube Propulsion Unit is a compact, modular propulsion system for CubeSats and SmallSats, offering various configurations to provide delta-v for collision avoidance, statio

Form Factor	3U
Form Factor	6U
Form Factor	12U
Form Factor	Smallsat
WaterCube Propulsion Unit Volume [U]	0.7U (baseline product)

price on requestdatasheet

China Great Wall Industry Corporation (CGWIC) provides space transportation, launch services, satellite communication, Earth observation, meteorological and navigation satellite solutions, and related

Chinese state-owned nuclear enterprise founded 1955 in Beijing overseeing civilian nuclear power, fuel production, and uranium mining; uses satellite remote sensing for exploration and researches nuclear space propulsion.

Small satellite propulsion systems developer specializing in electric and chemical thrusters for CubeSats and small spacecraft.

CU Aerospace

CHIPS — CubeSat High Impulse Propulsion System

Miniaturized warm-gas resistojet propulsion system for CubeSats with integrated main thruster and 3-axis ACS.

Thruster type	Warm-gas resistojet (superheater)
Specific impulse (Isp)	40–50% higher than cold-gas Isp
Total impulse (CHIPS-180)	180 N-s
Package size (without ACS)	As small as 0.3U
Package size (with ACS)	As small as 0.6U

price on requestdatasheet

CU Aerospace

CHIPS CubeSat High Impulse Propulsion System

Miniaturized propulsion combining main thruster with 3-axis attitude control — non-toxic self-pressurizing propellants, 120M+ valve actuations, 0.54U CHIPS-180 variant.

Propellant options	R236fa and R134a (range-safety approved)
CHIPS-180 size	0.54U
CHIPS-180 total impulse	180 N-s
Valve cycle life	>120 million actuations
Temperature rise	~1°C per 10-min cycle

price on request

CU Aerospace

FPPT — Fiber-Fed Pulsed Plasma Thruster

CU Aerospace’s Fiber-Fed Pulsed Plasma Thruster (FPPT) provides very high specific impulse greater than 3,500 seconds via a 10-microsecond electromagnetic pulse discharge usi

Thruster type	Pulsed plasma thruster (PPT) with electromagnetic thrust vectoring
Specific impulse (Isp)	>3,500 s
Total impulse (1.7L package)	>25,000 N-s
Total impulse range	1,000–600,000 N-s (0.7L–53L)
Package size range	0.7 L to 53 L (1U to ESPA-class)

price on request

CU Aerospace

FPPT Fiber-Fed Pulsed Plasma Thruster

High-Isp electric propulsion ablating spooled PTFE fiber via short pulses — >3,500s Isp, no pressurized tank, scales 0.7L-53L, for orbit maneuvers and debris removal.

Pulse duration	10 microseconds
Specific impulse	>3,500 s
Thrust vectoring range	±5° (pitch/yaw)
Total impulse (1.7L package)	>25,000 N-s
Size range	0.7L to 53L

price on request

CU Aerospace

MPUC Monopropellant Propulsion Unit for CubeSats

High-thrust monopropellant propulsion using proprietary CMP-X ethanol/hydrogen-peroxide blend — safer, lower-cost alternative to hydrazine, >2,000 Ns total impulse.

Propellant	CMP-X (ethanol/hydrogen peroxide)
Flame temperature	~900°C
Demonstrated Isp	178 s at 230 mN thrust
Continuous firing demonstrated	>50 minutes
Freeze temperature	<-33°C

price on request

d-start designs and manufactures engines with external energy sources for single-pulse orbital maneuvers of femto-class and pico-class spacecraft, including those utilizing space debris.

D-Start

Thrusters for very small satellites (Engines for ultra-small spacecraft)

A family of propulsion systems for femto-class and pico-class spacecraft, including ChipSats, designed for single-pulse orbital maneuvers using external energy sources, potentially

Type	Micro-propulsion engine
Target platform	CubeSat, microsatellite

price on requestdatasheet

New Zealand and Netherlands aerospace company developing the Mk-II Aurora reusable spaceplane and refuellable in-space propulsion systems for satellite missions.

Dawn Aerospace

B20 Thruster

A 20 N-class green bipropellant thruster from Dawn Aerospace using non-toxic nitrous oxide and propene propellants, designed for reliable, repeatable spacecraft propulsion from gro

Thrust range	6.46-18.11 N
Specific impulse (vacuum)	240-285+ s
Propellant	Nitrous oxide oxidizer / propene fuel, self-pressurizing non-toxic bipropellant
Restarts	10,000+ per thruster, unlimited cold starts
Ignition type	Spark-based, cold-start to full thrust in under 100 ms

price on request

Dawn Aerospace

Dawn Aerospace Green Chemical Propulsion Thrusters (B1, B5, B20, B200)

Dawn Aerospace offers a family of non-toxic 'green' chemical propulsion thrusters (B1, B5, B20, B200) using nitrous oxide and propene, designed for reliable and scalable spacecraft

Thrust, range	6.46 to 18.11 N (1.45 to 4.07 lbf)
Minimum impulse bit Bi-prop	0.98 N.s (0.22 lbf.s)
Cold-gas	10 mN.s (0.02 lbf.s)
Ignition	Spark-based igniter
Pulse frequency	4 Hz

price on requestdatasheet

Dawn Aerospace

Dawn Aerospace Thrusters (B1, B5, B20, B200)

Dawn Aerospace offers a range of non-toxic 'green' chemical propulsion thrusters (B1, B5, B20, B200) using nitrous oxide and propene, designed for various spacecraft sizes and miss

Thrust, range (B20)	6.46 to 18.11 N (1.45 to 4.07 lbf)
Minimum impulse bit (B20) Bi-prop	0.98 N.s (0.22 lbf.s)
Minimum impulse bit (B20) Cold-gas	10 mN.s (0.02 lbf.s)
Ignition (B20)	Spark-based igniter
Pulse frequency (B20)	4 Hz

price on requestdatasheet

Former US asteroid mining company (founded 2012), acquired by Bradford Space (NL) in 2019; Comet water electrolysis propulsion and Meteor green monopropellant thrusters for CubeSats and small satellites.

Deep Space Industries (Bradford Space)

Bradford ECAPS HPGP Thruster

Bradford Space's (formerly Deep Space Industries) High Performance Green Propellant (HPGP) thrusters — clean-burning, high-Isp alternatives to hydrazine for satellite attitude and

Propellant	LMP-103S (HPGP, green propellant)
Thrust Range	0.01 N – 22 N (product family)
Specific Impulse	220–240 s (~12% better than hydrazine)
Advantage	Non-toxic, cleaner handling, lower facility cost vs hydrazine
Flight Heritage	PRISMA (2010), ORBCOMM, numerous commercial smallsats

price on request

Deep Space Industries (Bradford Space)

Deep Space Industries Propulsion Systems

Bradford Space subsidiary developing in-space propulsion systems and resource utilization technology originally focused on asteroid mining concepts.

Focus	In-space propulsion systems
Parent	Bradford Space

price on request

Turkish aerospace company developing hybrid rocket propulsion, cryogenic systems, composite structures, and in-space propulsion — with a sounding rocket exceeding 200 km altitude and a hybrid propulsion system for Turkey's lunar hard landin

DELTAV Space Technologies

AYAP Lunar Propulsion System

DeltaV Space Technologies' hybrid propulsion system under development for Turkey's Lunar Hard Landing Mission (AYAP), designed for lunar descent braking.

Mission	Turkey Lunar Hard Landing Mission (AYAP)
Propulsion Type	Hybrid (solid fuel + liquid oxidizer)
Function	Lunar descent braking burn
Program Owner	Turkish Space Agency (TUA)
Status	Development

price on request

DELTAV Space Technologies

Hybrid Propulsion System (HIS)

A domestically-developed hybrid rocket propulsion system by DELTAV Space Technologies, designed for Turkey's AYAP-1 lunar hard-landing mission and adaptable to orbital missions.

Fuel type	High-performance solid fuel
Average thrust	650 N
Specific impulse	290 s
Firing duration	100+100 seconds (two burns)
Fuel mass	30 kg

price on request

DELTAV Space Technologies

SORS Sounding Rocket System

DeltaV Space Technologies' hybrid-propulsion sounding rocket — Turkey's first vehicle to exceed 200 km altitude and achieve in-space engine ignition.

Propulsion Type	Hybrid (solid fuel + liquid oxidizer)
Max Altitude Achieved	>200 km (June 2025)
Key Achievement	First hybrid propulsion in-space ignition; first Turkish rocket >200 km
Country	Turkey
Operator	DeltaV Space Technologies (subsidiary of SSB)

price on request

Developer of electrospray thrusters using nanomaterials science for efficient electric propulsion of small satellites and spacecraft.

DeltaX Propulsion

DeltaX Electrospray Thruster

High-efficiency electrospray thruster with 3,000 s Isp and 50% mass reduction via aerogel-integrated propellant.

Thruster type	Electrospray (electric propulsion)
Specific impulse (Isp)	~3,000 s (2–3x chemical thrusters)
Mass reduction	50% vs. comparable thrusters via aerogel-integrated propellant
Scalability	Modular design from CubeSats to GEO-class spacecraft

price on request

DeltaX Propulsion

DXP Electrospray Thruster

Carbon-aerogel electrospray thruster with Isp ~3,000 s for CubeSats and small satellites.

Specific Impulse (Isp)	~3,000 s
Propellant	Ionic liquid
Emitter Material	Carbon aerogel nanocomposite
Target Platform	1U–12U CubeSat
Thrust Mode	Electrospray / field emission

price on request

European defence manufacturer focused on scalable strike and air-defence systems for European and allied armed forces.

Destinus

Ruta Block 3

Long-range European deep-strike cruise system with in-house T220 turbojet propulsion at up to 2000 km range.

Range	up to 2000 km
Payload	250 kg
Propulsion	In-house T220 turbojet
Navigation	INS + GNSS + VNS + TERCON, GNSS-denied capable
Launch	Booster-assisted salvo from 40 ft container

price on request

Developer and producer of safe, electrically-throttled 'green' energetic materials and propellants for defense, space, and commercial markets.

Digital Solid State Propulsion

AF-M315E (ASCENT)

AF-M315E (ASCENT) is a high-performance, less toxic green monopropellant developed by AFRL and licensed to DSSP, offering an alternative to hydrazine for propulsion systems.

Item #	315-10
Qty	10lb (1gal)
Price	$3850
Item #	315-50
Qty	50lb (5gal)

$3 850datasheet

Digital Solid State Propulsion

AF-M315E (ASCENT) Green Monopropellant

HAN-based green liquid monopropellant, higher performance and lower toxicity than hydrazine, used in NASA GPIM.

Appearance	Translucent, light pink-orange liquid
Specific Gravity	1.46
Freezing Point	Does not freeze; glasses at -80°C
pH	3.7-4.0
Viscosity	23 cP at 25°C

$385 010datasheet

Digital Solid State Propulsion

GEM (Green Electric Monopropellant)

HAN-based liquid monopropellant family, electrically ignitable or catalyst-bed ignitable, in GEM3 and Sierra GEM variants.

Chemical basis	Hydroxylammonium nitrate (HAN)-based liquid monopropellant
Ignition method	Electric ignition or catalyst bed ignition
Hazard classification	1.4C
Variants	GEM3 (propulsion-grade, comparable to AF-M315E); Sierra GEM (high-temperature stability, o
Regulatory requirement	Current ATF permit and end-user agreement required for purchase

price on requestdatasheet

Digital Solid State Propulsion

GEM3 Green Electric Monopropellant

HAN-based electrically-ignited monopropellant, comparable to AF-M315E with faster ignition.

Appearance	Clear, pink solution
Viscosity	Approximately 20 centipoise at 25°C
pH	2 to 4
Decomposition Temperature	Approx. 170°C
Melting/Freezing Point	Less than 0°C (32°F)

$100 100datasheet

Indian space startup pioneering green propulsion systems for CubeSats and small satellites.

DREAM Aerospace

ATOM

ATOM is a next-generation monopropellant thruster designed for CubeSats, offering high-performance thrust starting from 1N using an eco-friendly, non-toxic propellant.

Minimum Thrust	1 N
Compatible Platforms	1U to 26U+ CubeSats
Propellant	Green monopropellant (nontoxic)

price on request

DREAM Aerospace

ATOM Monopropellant Thruster

Next-generation monopropellant thruster using eco-friendly, nontoxic propellant — starting from 1N thrust, for 1U to 26U+ CubeSats, 30x more agile than electric propulsion.

Thrust	Starting from 1N
Compatible platforms	1U to 26U+ CubeSats
Propellant	Eco-friendly, nontoxic monopropellant

price on request

DREAM Aerospace

CubeHood

CubeHood is an all-in-one propulsion module for CubeSats, designed for seamless integration with ATOM and providing complete thrust control for missions ranging from 1U to 26U+.

Compatible Platforms	1U to 26U+ CubeSats
Includes	Fuel tanks, thrust control, ATOM thruster integration

price on request

Austrian manufacturer of Field Emission Electric Propulsion (FEEP) systems for nano- and microsatellites, with over 200 propulsion units delivered to orbit.

ENPULSION GmbH

Cluster of IFM Nano Thruster for Smallsats

The IFM Nano thruster was developed as spin-off from a thruster being developed for high precision control of ESA’s Next Generation of satellite Gravity Missions. Building on more…

Manufacturer	ENPULSION
Lead time	12 weeks

price on request

ENPULSION GmbH

ENPULSION NANO Thruster (IFM Nano Thruster)

Self-contained indium FEEP electric propulsion system for CubeSats — up to 0.35 mN thrust, 2,000–6,000 s Isp, 680 g dry mass, >5,000 N·s total impulse.

Thrust Range	0.01–0.35 mN
Specific Impulse	2,000–6,000 s
Input Power	8–40 W (3.5 W hot standby)
Dry Mass	680 g
Wet Mass	900 g

price on requestdatasheet

ENPULSION GmbH

IFM Nano Thruster for CubeSats

With its IFM Nano Thruster ENPULSION was the first company to offer an operational FEEP-based propulsion solution, which was developed under ESA contracts for 15 years. Due to the…

Manufacturer	ENPULSION
Lead time	16 weeks

€38 400

EREMS is a French SME founded in 1979, specializing in the design and realization of electronic equipment and software for high technology fields including Space.

EREMS

PPSU Plasma Propulsion Selection Unit

Switching unit routing electrical power between electric propulsion power supplies and thrusters — routes signals from two PPUs to a single thruster.

Function

Switches thruster/cathode signals from 2 PPUs to a single thruster

price on request

SSC Space designs and launches sounding rockets and balloon systems, provides global ground station services, and offers engineering, operations, and consultancy for space missions.

Esrange Space Center (SSC)

Esrange Suborbital and Small Satellite Launch Services

Esrange Space Center's sounding rocket launch services, stratospheric balloon campaigns, and new small satellite orbital launch infrastructure near Kiruna, Sweden.

Location	Kiruna, Sweden (68°N, Arctic Circle)
Services	Sounding rockets, stratospheric balloons, (new) small satellite orbital launches
Science Advantage	Aurora access, polar ionosphere, polar vortex balloon trajectories
Operator	Swedish Space Corporation (SSC)
New Capability	SSO and polar orbital launch for small satellites (in development)

price on requestdatasheet

US developer of miniaturized Hall effect thrusters and propellant distribution systems for high-impulse, affordable microsatellite and CubeSat propulsion.

ExoTerra Resource

HALO THRUSTERS

ExoTerra's HALO THRUSTERS product line includes the Halo 8 and Halo 12 Hall-Effect Thrusters, designed for small satellites to achieve optimal orbits, extend mission lifetimes, and

Flight Heritage	As of July 1, 2023, four Halo-based integrated propulsion systems are operating in orbit.
Propellant (Halo 8)	Xenon
Mass (Halo 8)	0.83 kg
Volume (Halo 8)	0.375 U
Input Power (Halo 8)	100 – 450 W

price on requestdatasheet

ExoTerra Resource

Iris Propulsion Module / Propulsion Kit

ExoTerra offers the Iris Propulsion Module, a bolt-on solar electric propulsion system for small spacecraft, and a Propulsion Kit consisting of a Hall-effect thruster, Power Proces

Radiation Tolerance (Iris)	30 kRad TID
Propellant Options (Iris)	Xenon or Krypton
Mounting (Iris)	Inside a standard 24” Lightband
Height (Iris)	Less than 30 cm
Operational Power (Iris)	Low sub-kilowatt levels

price on requestdatasheet

French electric propulsion company; ExoMG™ Hall thrusters for satellite orbit raising, station-keeping, and deorbit; SpaceCloud OTV and SpaceOps software.

Exotrail

ExoMG Hall Effect Thruster

ExoMG is Exotrail’s Hall effect electric thruster designed for small satellites from 20 kg to 500 kg class. Hall effect thrusters use a magnetic field to ionize xenon propell

price on request

Exotrail

SpaceVan Electric Propulsion Transfer System

Exotrail's SpaceVan — an in-space propulsion transfer vehicle combining Hall-effect thrusters for delivering satellite payloads from rideshare drops to their operational orbits.

Propulsion Type	Hall-effect (xenon) electric propulsion
Thruster Family	ExoMG (1–15 mN thrust, 1,000–1,800 s Isp)
Power Range	<300 W
Function	Last-mile orbit delivery (rideshare → operational orbit)
Transfer Time	Weeks to months (vs. hours for chemical)

price on request

Exotrail

spaceware™ Hall Effect Thruster

spaceware™ is a next-generation Hall Effect thruster designed for versatility and power, featuring a modular architecture for easy integration into diverse satellite platforms and

Thrust	2.5 mN
Power	60 W
Total Impulse	Up to 6 kN.s
ON/OFF cycles	3,000 cycles
Lifetime	5 years In-Orbit

price on request

Developer of multimode chemical-electric propulsion systems for small satellites.

Gama Space develops solar sail propulsion for low-cost deep space missions and Astrobrake, an autonomous drag sail for satellite deorbiting compliance.

Gama Space

Solar Sail

Gama Space offers low-cost, reliable, and scalable solar sails designed for deep space access and various mission requirements.

price on request

Austrian manufacturer of high-thrust chemical propulsion systems for satellite mobility and orbit control.

GATE Space

GATE Jetpack

GATE Jetpack is a plug-and-play chemical propulsion module for ESPA-class satellites, providing orbit transfer, attitude control, collision avoidance, refueling support and deorbit

Total impulse (Jetpack S)	36,000 Ns
Lead time (Jetpack S)	9 months
Price (Jetpack S)	€450,000
Thrusters (Jetpack S)	4 × [1 – 6 N]
Thrust modes (Jetpack S)	Continuous — Pulsed — Cold gas — Deep throttling 1:10

price on request

GATE Space

GATE Jetpack L

Largest plug-and-play high-thrust propulsion module for ESPA-class satellites, full-port XL configuration.

Total impulse	140,000 Ns
Lead time	9 months
Thrust level	4 × [20 N]
Propellants	C2H6 and N2O
Specific impulse	270 s – 300 s

price on request

GATE Space

GATE Jetpack M

Mid-size plug-and-play high-thrust propulsion module for ESPA-class satellites, full-port configuration.

Total impulse	80,000 Ns
Lead time	9 months
Thrust level	4 × [20 N]
Propellants	C2H6 and N2O
Specific impulse	270 s – 300 s

price on request

GATE Space

GATE Jetpack S

The GATE Jetpack S is a plug-and-play chemical propulsion system designed for ESPA-class satellites, offering 36,000 Ns total impulse for orbit transfers, mission reconfigurations,

Total Impulse	36,000 Ns
Lead Time	9 months
Price	€450,000
Thrusters	4 × [1 – 6 N]
Operating Modes	Continuous — Pulsed — Cold gas — Deep throttling 1:10

€450 000

GATE Space

GATE Thruster L

High-precision chemical thruster with closed-loop pressure control, 20-200 N thrust range.

Thrust level	20 – 200 N
Lead time	9-12 months
Base price	€50,000
Throttling ratio	1:10
Minimum impulse bit	2 Ns

€50 000

GATE Space

GATE Thruster S

Compact high-precision chemical thruster with closed-loop pressure control, 2-20 N thrust range.

Thrust level	2 – 20 N
Lead time	9-12 months
Base price	€30,000
Throttling ratio	1:10
Operational modes	Continuous — Pulsed — Cold gas

€30 000

Italian deep-tech propulsion company — propellant-free electromagnetic propulsion system, TRL 7-8, 1,328 hours on-orbit validated across GEN-01/02/03 on SpaceX Transporter missions.

Genergo

Genergo Propellant-Free Electromagnetic Propulsion System

Propellantless electromagnetic propulsion for satellites — converts electrical energy directly into thrust, no fuel required. TRL 7-8 with 1,328 on-orbit hours across GEN-01/02/03

Propellant required	None — propellantless electromagnetic system
Energy source	Electrical energy only
Hazardous materials	None
Pressurization hardware	None required
TRL	7-8

price on request

Gilmour Space Technologies builds and operates an integrated launch vehicle, satellite platform, and spaceport for commercial, government, and defence customers.

Gilmour Space Technologies

Sirius Rocket Engine Family

Gilmour Space Technologies' Sirius hybrid rocket engine family — the in-house propulsion powering the Eris launch vehicle's upper stage and test program.

Engine Type	Hybrid (LOX oxidizer + solid hydrocarbon fuel grain)
Application	Eris upper stages (2nd and 3rd stage)
Testing	Multiple static fires, Helensvale QLD facility
Launch Vehicle	Eris (3-stage rocket, ~305 kg to SSO)
Launch Site	Bowen Space Launch Facility, North Queensland, Australia

price on request

Glavkosmos coordinates international human spaceflight projects, facilitates satellite launches, develops and supplies rocket components, and provides equipment for space crews.

Glavkosmos

3TU Thruster Unit

The 3TU Thruster Unit is a hydrazine-fueled propulsion system designed for spacecraft orientation and attitude control, featuring eight thermocatalytic low thrusters.

Purpose	Spacecraft orientation and attitude control.
Year of release	1999
Guaranteed service life	10.5 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes

price on request

Glavkosmos

Adjustment and Braking Engine

The Adjustment and Braking Engine is a four-chamber propulsion system designed for unmanned spacecraft reactive control, orbit control, and braking maneuvers, utilizing UDMH/NTO pr

Purpose	Unmanned Spacecraft reactive control system
Year of release	2010
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Propellants, Fuel/Oxidizer	UDMH/NTO

price on request

Glavkosmos

Attitude Control Propulsion Unit

The Attitude Control Propulsion Unit is a xenon-fueled propulsion system designed for generating steering effort in spacecraft attitude and survivability modes.

Year of release	2003
Guaranteed service life (years)	19
Estimated production / delivery time (months)	7
Operating propellant	Xenon (State Standard GOST 10219-77)
Nominal nozzle thrust, N (gf)	7.85×10-2 (8)

price on request

Glavkosmos

Attitude Control Thruster Unit Based on Modified Thermocatalytic Low Thrusters

A spacecraft attitude control thruster unit utilizing two modified thermocatalytic low thrusters, designed for orientation and attitude adjustments.

Year of release	2009
Guaranteed service life	10 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes
Possibility to adapt the product to customer requirements	Yes

price on request

Glavkosmos

Attitude Control Thruster Unit Based on Thermocatalytic Low Thrusters

A thermocatalytic low thruster unit designed for spacecraft orientation and attitude control, using hydrazine propellant.

Purpose	Spacecraft orientation, attitude control.
Year of release	1999
Guaranteed service life (years)	10.5
Estimated production / delivery time (months)	12
Flight qualification of the product	Yes

price on request

Glavkosmos

Bipropellant Low Thrust Rocket Engine

A bipropellant low-thrust rocket engine, flight-qualified and adaptable to customer requirements, released in 1996.

Year of release	1996
Flight qualification of the product	Letter "O1", flight use
Possibility to adapt the product to customer requirements	Yes

price on request

Glavkosmos

Bipropellant Tank with Stiff-Plastic Separation Devices (Diaphragms)

A bipropellant tank with stiff-plastic separation devices (diaphragms) designed for the KDU 11D414HC propulsion system of communication satellites, qualified for flight use.

Purpose	KDU 11D414HC propulsion system for communication satellite.
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Propellants, Fuel/Oxidizer	UDMH/NTO
Operating Pressure, not over	2.94 MPa

price on request

Glavkosmos

Bipropellant Thruster

A bipropellant thruster designed for the Briz-M booster, providing attitude control for spacecraft using UDMH/NTO propellants.

Purpose	Briz-M booster
Year of release	2005
Flight qualification of the product	Letter "O", flight use
Brief history of flight qualification	By the beginning of 2019 the11D458M thrusters numbering 260 have provided successful servi
Possibility to adapt the product to customer requirements	Yes

price on request

Glavkosmos

Bipropellant Thruster 11d

The Bipropellant Thruster 11d is a flight-qualified propulsion unit designed for spacecraft attitude control, utilizing UDMH/NTO propellants.

Purpose	Phobos Sample Return Spacecraft
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Propellants, Fuel/Oxidizer	UDMH/NTO
Nominal Thrust	53.9 N

price on request

Glavkosmos

Bipropellant Thruster 17D

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.

Purpose	Multi-impulse attitude control of spacecraft in response to control system triggering comm
Year of release	1985
Flight heritage	ALMAZ orbital station; BRIZ booster units; KVANT-2, KRISTALL, SPEKTR, PRIRODA (MIR station
Customization	Can be adapted to customer requirements
Propellants	UDMH / NTO

price on request

Glavkosmos

Cold Ammonia Corrective Propulsion System

A cold-gas ammonia corrective propulsion system (CPS) for correcting and stabilizing spacecraft orbit parameters and zeroing the kinetic moment of flywheel engines in the orientati

Year of release	2014
Guaranteed service life (years)	5
Estimated production / delivery time (months)	12
Flight qualification of the product	Da
Brief history of flight qualification	Components in the spacecraft "Meteor" and "Electro".

price on request

Glavkosmos

Composite Storage Tank

A flight-qualified composite storage tank designed for storing propellants like Xenon, Nitrogen, Air, and Helium, primarily for feeding electrical thrusters.

Purpose	Xenon storage unit.
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Working medium	Xenon, Nitrogen, Air, Helium
Operating Pressure, not over	14.2 MPa

price on request

Glavkosmos

Composite Vessel

A flight-qualified composite vessel designed for spacecraft propulsion systems, capable of storing and feeding pressurant to propellant tanks and operating fluid to cold gas thrust

Purpose	Phobos Sample Return Mission - International Program: Return Spacecraft Propulsion System
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Working medium	Nitrogen, Air, Helium
Operating Pressure, not over	17.6 MPa

price on request

Glavkosmos

Cool Gas Thruster

A cool gas thruster designed for precise spacecraft orientation, featuring small size and mass, and capable of generating multiple impulses.

Purpose	KOSMOS and RESURS-DK spacecraft
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Working medium	helium/nitrogen
Nominal Thrust	0.733/0.819 N

price on request

Glavkosmos

Correction Unit (CU) based on Stationary Plasma Thruster with a Nominal Discharge Power of 1350 W and XFC Unit

A Correction Unit (CU) featuring a Stationary Plasma Thruster with 1350 W nominal discharge power and a Xenon Flow Controller Unit (XFC Unit), designed for spacecraft station keepi

Purpose	Spacecraft station keeping. Spacecraft orbit raising to GEO
Year of release	1995
Guaranteed service life (years)	9000 hours 5000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	Yes

price on request

Glavkosmos

Corrective Propulsion System 95

The AIPD-95 corrective propulsion system is designed for spacecraft orbit correction and maintenance, featuring a pulsed operating mode with a 1 Hz pulse repetition rate.

Purpose	The AIPD-95 corrective propulsion system is designed to perform the correction of the orbi
Year of release	2009
Guaranteed service life	7 years
Estimated production / delivery time	12 months
Flight qualification of the product	No

price on request

Glavkosmos

Corrective Propulsion System UD-AIPD

The UD-AIPD is a corrective propulsion system designed for spacecraft orientation and correction, featuring a monoblock design and operating in a pulsed mode.

Purpose	The corrective propulsion system UD-AIPD is intended for use as part of systems for the co
Year of release	2007
Guaranteed service life	15 years
Estimated production / delivery time	12 months
Flight qualification of the product	No

price on request

Glavkosmos

Dual-mode Stationary Plasma Thruster with a Nominal Discharge Power of 2500/1350 W

A dual-mode stationary plasma thruster with nominal discharge powers of 2500W and 1350W, designed for spacecraft station keeping and orbit raising to GEO.

Purpose	Spacecraft station keeping. Spacecraft orbit raising to GEO.
Year of release	2007
Guaranteed service life (years)	8000 / 12000 hours 5000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	No

price on request

Glavkosmos

EJK Solenoid Valve

The EJK Solenoid Valve is a single-stage, multi-starting, normally closed, single-seat, teflon seal valve designed for remote flow control of liquid and gaseous working media, incl

Purpose	Flow remote control of liquid and gaseous working media (NTO, UDMH, water, alcohol, freon,
Flight qualification of the product	Letter "O1", flight use
Possibility to adapt the product to customer requirements	Yes
Internal Diameter	1.6 mm
Water Flow Rate / Hydraulic Resistance	22.5 g/s/not over 0.2 MPa

price on request

Glavkosmos

Electric Thruster for Spacecraft with Mass up to 1500 kg

An electric thruster designed for spacecraft up to 1500 kg, offering high specific impulse at relatively low power and a long service life.

Purpose	Propulsion system of spacecraft by mass up to 1500 kg.
Year of release	2012
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	Yes

price on request

Glavkosmos

Electric Thruster for Spacecraft with Mass up to 2500-3000 kg

This is an electric Hall-effect thruster designed for spacecraft with a mass of up to 2500-3000 kg, offering high specific impulse and a long service life.

Purpose	Propulsion system of spacecraft by mass up to 2500 - 3000 kg.
Year of release	2018
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	No

price on request

Glavkosmos

Electric Thruster for Spacecraft with Mass up to 3000 kg

An electric thruster designed for spacecraft up to 3000 kg, featuring high specific impulse and W-Ba emitter-based cathodes.

Purpose	Propulsion system of spacecraft by mass up to 3000 kg.
Year of release	2011
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	No

price on request

Glavkosmos

Electric Thruster for Spacecraft with Mass up to 3000 kg 1

This is an electric, multimode thruster designed for spacecraft up to 3000 kg, featuring W-Ba emitter cathodes and a guaranteed service life of 15 years in GSO.

Purpose	Propulsion system of spacecraft by mass up to 3000 kg.
Year of release	2002
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	Yes

price on request

Glavkosmos

Electric Thruster for Spacecraft with Mass up to 500 kg

An electric thruster designed for spacecraft up to 500 kg, offering high efficiency at low power.

Purpose	Propulsion system of spacecraft by mass up to 500 kg.
Year of release	2004
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	Yes

price on request

Glavkosmos

Electrically Powered Cruise Engine

An electrically powered cruise engine designed for spacecraft, offering 520 mN of thrust and a specific impulse of 2580 seconds.

Purpose	Transportation tasks
Year of release	2018
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	No

price on request

Glavkosmos

Gas Feed Unit

The Gas Feed Unit is a pneumatic automation equipment designed to supply Xenon propellant at a specified pressure and flow rate to orbit control propulsion units.

Purpose	Providing Xenon at the specified pressure and flow rate to the orbit control propulsion un
Year of release	2003
Guaranteed service life	19 years
Estimated production / delivery time	9 months
Flight qualification of the product	No

price on request

Glavkosmos

High Pressure Electric Valve

This High Pressure Electric Valve is designed for opening and closing low-pressure gas paths, suitable for applications requiring precise control of gas flow.

Year of release	2001
Guaranteed service life (years)	19
Estimated production / delivery time (months)	5
Operating pressure, kg/cm2	up to 250
Electric valve supply voltage, opening, V	23 - 34

price on request

Glavkosmos

High-powered Electric Thruster for Spacecraft with Mass up to 3000 kg

This is a high-powered, multimode electric thruster designed for spacecraft up to 3000 kg, featuring W-Ba emitter cathodes.

Purpose	Propulsion system of spacecraft by mass up to 3000 kg.
Year of release	2001
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	No

price on request

Glavkosmos

Integrated Thruster Unit 13

The Integrated Thruster Unit 13 (ITU) is a propulsion system designed for spacecraft orbit formation and station keeping, featuring a high-precision thruster orientation mechanism

Purpose	ITU is intended for creating the required thrust forces when forming the spacecraft operat
Year of release	2008
Guaranteed service life (years)	15
Estimated production / delivery time (months)	14
Flight qualification of the product	No

price on request

Glavkosmos

Integrated Thruster Unit ITU-5000M

The ITU-5000M is an integrated thruster unit designed for spacecraft orbit formation and station keeping, featuring a high-precision Thruster Orientation Mechanism and a Modified S

Purpose	ITU-5000M is intended for creating the required thrust forces when forming the spacecraft
Year of release	2008
Guaranteed service life (years)	15
Estimated production / delivery time (months)	14
Flight qualification of the product	No

price on request

Glavkosmos

Low Emission Electric Valve

A low emission electric valve designed for opening and closing high and low pressure gas paths, suitable for spacecraft applications.

Purpose	Designed for opening and closing of high and low pressure gas paths.
Year of release	2008
Guaranteed service life	19 years
Estimated production / delivery time	5 months
Operating pressure	250 kg/cm2

price on request

Glavkosmos

Low Power Stationary Plasma Thruster

A low-power stationary plasma thruster designed for spacecraft station keeping, utilizing xenon propellant and featuring a hollow cathode.

Purpose	Spacecraft (S/C) station keeping.
Year of release	2009
Guaranteed service life (years)	1000 hours 2000 vklyucheniy
Estimated production / delivery time (months)	10
Flight qualification of the product	No

price on request

Glavkosmos

Low Power Stationary Plasma Thruster with 50 mm Diameter of the Accelerating Channel

A low-power stationary plasma thruster with a 50 mm accelerating channel diameter, designed for spacecraft station keeping and utilizing xenon propellant.

Purpose	Spacecraft (S/C) station keeping.
Year of release	1976
Guaranteed service life (years)	2500 hours 3000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	Yes

price on request

Glavkosmos

Low Power Stationary Plasma Thruster with 70 mm Diameter of the Accelerating Channel

A low-power stationary plasma thruster designed for spacecraft position keeping, utilizing xenon propellant and featuring a classical magnetic system.

Purpose	Spacecraft position keeping.
Year of release	1980
Guaranteed service life (years)	3100 hours 3000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	Yes

price on request

Glavkosmos

Low Pressure Electric Valve

A low-pressure electric valve designed for opening and closing gas paths, suitable for spacecraft applications.

Year of release	2001
Guaranteed service life	19 years
Estimated production / delivery time	5 months
Operating pressure	up to 5 kg/cm2
Electric valve supply voltage, opening	24 - 34 V

price on request

Glavkosmos

Metal Composite Xenon Tank XT-200

The Metal Composite Xenon Tank XT-200 is a high-pressure storage vessel designed for xenon propellant in electric propulsion systems, enabling spacecraft orbit raising.

Year of release	2015
Guaranteed service life	19 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes
Possibility to adapt the product to customer requirements	Yes

price on request

Glavkosmos

Metal Composite Xenon Tank XT-350

The Metal Composite Xenon Tank XT-350 is a flight-qualified, metal-composite tank designed to store xenon for electric propulsion systems on spacecraft, enabling orbit raising mane

Purpose	In apogee electric propulsion engine units to provide spacecraft orbit raising from geosta
Year of release	2012
Guaranteed service life	19 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes

price on request

Glavkosmos

Modified Low Power Stationary Plasma Thruster with 50 mm Diameter of the Accelerating Channel

A modified low-power stationary plasma thruster with a 50 mm accelerating channel, designed for spacecraft station keeping and flight-qualified on OneWeb satellites.

Purpose	Spacecraft (S/C) station keeping.
Year of release	2016
Guaranteed service life (years)	5000 hours 6000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	Yes

price on request

Glavkosmos

Modified Low Power Stationary Plasma Thruster with 70 mm Diameter of the Accelerating Channel

A modified low-power stationary plasma thruster designed for spacecraft station keeping, featuring a 70 mm accelerating channel and using xenon propellant.

Purpose	Spacecraft (S/C) station keeping.
Year of release	2015
Guaranteed service life (years)	7000 hours 7000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	No

price on request

Glavkosmos

Modified Stationary Plasma Thruster with a Discharge Power of up to 5 kW

A modified stationary plasma thruster with a discharge power of up to 5 kW, designed for spacecraft station keeping and orbit raising to GEO, using xenon propellant.

Purpose	Spacecraft station keeping. Spacecraft orbit raising to GEO.
Year of release	2007
Guaranteed service life (years)	20000 hours 7000 cycles
Estimated production / delivery time (months)	12
Flight qualification of the product	Yes

price on request

Glavkosmos

Modified Stationary Plasma Thruster with a Nominal Discharge Power of 1350 W

A modified Stationary Plasma Thruster (SPT) with a nominal discharge power of 1350 W, designed for spacecraft station keeping and orbit raising using xenon propellant.

Purpose	Spacecraft station keeping. Spacecraft orbit raising to GEO.
Year of release	2012
Guaranteed service life (years)	12000 hours 5000 cycles
Estimated production / delivery time (months)	10
Flight qualification of the product	No

price on request

Glavkosmos

Modified Thermocatalytic Low Thruster

A hydrazine monopropellant thermocatalytic thruster used for spacecraft orientation, attitude control, and station keeping, with flight-qualified heritage on multiple Russian satel

Purpose	Spacecraft orientation, attitude control, and station keeping
Year of release	2009
Guaranteed service life (years)	10.5
Estimated production / delivery time (months)	10
Flight qualification of the product	Yes

price on request

Glavkosmos

Modified Thermocatalytic Thrusters

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 va

Thrust	(5.6 … 1.0) N
Propellant inlet pressure	(883..204) kPa
Specific impulse in a continuous mode of operation	(220..214) s
Life in terms of propellant throughput, kg	20 kg
Life in terms of number of cycles	50 cycles

price on request

Glavkosmos

Monopropellant Tank with Stiff-Plastic Separation Device (Diaphragm)

A monopropellant tank with a stiff-plastic separation device (diaphragm) designed for spacecraft propulsion systems, capable of storing and feeding UDMH and NTO propellants.

Purpose	Phobos Sample Return Mission - International Program: Return Spacecraft Propulsion System.
Year of release	2011
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Propellant	UDMH, NTO

price on request

Glavkosmos

MULTI-LAYER BELLOWS

Multi-layer bellows designed for use as sensing elements, phase separators, sealing devices, and power unit components in various atmospheres, particularly suitable for liquid rock

Purpose	Intended for operation as sensing elements, phase separators, sealing devices as well as p
Year of release	2007
Guaranteed service life (years)	6
Estimated production / delivery time (months)	2
Flight qualification of the product	No

price on request

Glavkosmos

Multichannel Electric Thruster

A high-power multichannel electric thruster designed for spacecraft propulsion systems, offering thrust up to 600 mN and a specific impulse of 1500-4000 s.

Purpose	High-power propulsion systems of spacecraft.
Guaranteed service life (years)	15 (GSO)
Estimated production / delivery time (months)	12
Flight qualification of the product	No
Brief history of flight qualification	Laboratory model.

price on request

Glavkosmos

Pressure Alarm

A pressure alarm designed to generate an alarm signal when overpressure exceeds the maximum permissible level, suitable for pneumatic automation equipment.

Year of release	2001
Guaranteed service life	19 years
Estimated production / delivery time	3 months
Operating pressure	4.5 kg/cm2
Electric valve supply voltage, opening	3.6-4.4 V

price on request

Glavkosmos

Pressure Reducer. Type 1

The Type 1 Pressure Reducer is a pneumatic automation component designed for propellant pressure reduction in spacecraft, offering a guaranteed service life of 19 years.

Year of release	2001
Guaranteed service life (years)	19
Estimated production / delivery time (months)	5
Propellant flow rate, mg/s	1.5 to 17
Inlet operating pressure (excess), kgf/cm2	250 to 5

price on request

Glavkosmos

Pressure Reducer. Type 2

The Pressure Reducer Type 2 is a pneumatic automation equipment designed for propellant pressure reduction in spacecraft propulsion systems.

Purpose	Propellant pressure reduction.
Year of release	2001
Guaranteed service life	19 years
Estimated production / delivery time	5 months
Propellant flow rate	4 to 15 mg/s

price on request

Glavkosmos

Pressure Reducer. Type 3 (for pressure integrity check unit)

A Type 3 pressure reducer designed for propellant pressure reduction, suitable for use in pressure integrity check units.

Purpose	Propellant pressure reduction.
Year of release	2003
Guaranteed service life	19 years
Estimated production / delivery time	5 months
Propellant flow rate	0.2 to 1.2 mg/s

price on request

Glavkosmos

Pressure Reducing Electric Valve

An electric valve designed to open, close, and reduce high-pressure gas lines, maintaining a specified low pressure range.

Purpose	Opening and closing of the high pressure gas line, pressure reduction from high to low and
Year of release	1985
Guaranteed service life	12 years
Estimated production / delivery time	9 months
Propellant flow rate	0.036 to 9 kg/h

price on request

Glavkosmos

Pressure Sensor 100

The Pressure Sensor 100 is a piezoresistive sensor designed for measuring absolute slowly varying pressure of liquid and gaseous media in spacecraft propulsion units and on-board s

Range of measurements	0-0,245; 0-0,588; 0-0,98; 0-1,47; 0-24,5 Mpa
The basic error (depending on the order)	0,5-1,5 %
Output signal	28-33 mV
Supply Current	2,78±0,02 mA
Weight	0,04 kg

price on request

Glavkosmos

Pressure Sensor Vt 212

The Pressure Sensor Vt 212 is a strain gauge sensor designed for measuring static-dynamic pressure in liquid and gaseous aggressive and non-aggressive media within liquid rocket en

Purpose	Measurement of the static-dynamic pressure of liquid and gaseous aggressive and non-aggres
Estimated production / delivery time	6 months
Flight qualification of the product	Yes
Possibility to adapt the product to customer requirements	Yes
Range of measurements	0-2,8; 0-4; 0-5,6; 0-8; 0-11; 0-16; 0-22; 0-30; 0-45; 0-60; 0-90; 0-125 Mpa

price on request

Glavkosmos

Pressure Stabilization Unit

The Pressure Stabilization Unit (PSU) is a flight-qualified component designed to maintain stable propellant pressure for spacecraft propulsion systems, utilizing hydrazine propell

Purpose	Pressure Stabilization
Year of release	2009
Guaranteed service life	10 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes

price on request

Glavkosmos

Propellant Management Assembly (PMA)

The Propellant Management Assembly (PMA) reduces high-pressure propellant and supplies it from a storage unit to an XFC within a required pressure range, specifically for stationar

Guaranteed service life	10 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes
Possibility to adapt the product to customer requirements	Yes
Maximum inlet pressure at a temperature of 40 °C	190 kgf/cm2

price on request

Glavkosmos

Propulsion System [PS] for Nanosatellite Platform

The Propulsion System (PS) for Nanosatellite Platform is an electrothermal propulsion unit designed for orbital maneuvering of cubesat-class spacecraft.

Year of release	2016
Guaranteed service life	3 years
Estimated production / delivery time	12 months
Flight qualification of the product	No
Possibility to adapt the product to customer requirements	Yes

price on request

Glavkosmos

RD-120MS

RD-120MS is a modification of the RD-120 liquid rocket engine with afterburning of oxidizing gas, intended for the upper stages of promising Russian and foreign launch vehicles.

Thrust, earth / void, tf	- / 93
Specific impulse, earth / void, s	- / 351
Pressure in the combustion chamber, kgf/cm2	181.6
Weight, dry / dipped, kg	1450/1610
Dimensions height / diameter, mm	4714/2600

price on request

Glavkosmos

RD-171 M

The RD-171 M is a powerful liquid rocket engine designed for the first stage of the Zenit launch vehicle, utilizing oxygen and kerosene propellants with an afterburning oxidizing g

Purpose	Engines for the first stage of the Zenit launch vehicle.
Year of release	2004
Guaranteed service life (years)	8 renewable
Estimated production / delivery time (months)	22
Flight qualification of the product	Yes

price on request

Glavkosmos

RD-180

The RD-180 is a liquid rocket engine with afterburning of oxidizing gas, designed for the first stage of the Atlas launch vehicle family, using oxygen and kerosene as propellants.

Purpose	Engines for the first stage of the Atlas launch vehicle family.
Year of release	1999
Guaranteed service life	10 years
Estimated production / delivery time	18 months
Flight qualification of the product	Yes

price on request

Glavkosmos

RD-181

The RD-181 is a liquid rocket engine with afterburning of oxidizing gas, designed for the first stage of the Antares launch vehicle, using oxygen and kerosene as propellants.

Purpose	Engines for the first stage of the advanced Antares launch vehicle.
Year of release	2015
Guaranteed service life	11 years
Estimated production / delivery time	14 months
Flight qualification of the product	Yes

price on request

Glavkosmos

RD-182 (120M)

The RD-182 (120M) is a liquid-propellant rocket engine, a terrestrial modification of the RD120MS, designed for the first stages of promising Russian and foreign launch vehicles.

Purpose	For the first stages of promising Russian and foreign launch vehicles.
Year of release	2022
Flight qualification of the product	No
Possibility to adapt the product to customer requirements	No
Thrust, earth / void	79/89 tf

price on request

Glavkosmos

Solenoid Valves 12 PT

The Solenoid Valves 12 PT are single-stage, multi-starting, normally closed valves with a Teflon seal, designed for remote flow control of various liquid and gaseous media, includi

Purpose	Flow remote control of liquid and gaseous working media (NTO, UDMH, water, alcohol, freon,
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Internal Diameter	0.6 mm
Water Flow Rate / Hydraulic Resistance	2.43 g/s/not over 0.127 MPa

price on request

Glavkosmos

Solenoid Valves 12 PT-01

The Solenoid Valves 12 PT-01 are single-stage, multi-starting, normally closed valves with a Teflon seal, designed for remote flow control of liquid and gaseous working media in sp

Purpose	Flow remote control of liquid and gaseous working media (NTO, UDMH, water, alcohol, freon,
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Internal Diameter	0.7 mm
Water Flow Rate / Hydraulic Resistance	2.43 g/s/not over 0.039 MPa

price on request

Glavkosmos

Solenoid Valves 26 RT-200

The 26 РТ-200 Solenoid Valve is a single-stage, multi-starting, normally closed valve with a Teflon seal, designed for remote flow control of various liquid and gaseous working med

Purpose	Flow remote control of liquid and gaseous working media (NTO, UDMH, kerosene, water, alcoh
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Internal Diameter	2.8 mm
Water Flow Rate / Hydraulic Resistance	71 g/s/not over 0.09 MPa

price on request

Glavkosmos

Solenoid Valves RT 200-00-01

The Solenoid Valves РТ 200-00-01 are single-stage, multi-starting, normally closed valves with a teflon seal, designed for remote flow control of various liquid and gaseous working

Purpose	Flow remote control of liquid and gaseous working media (NTO, UDMH, kerosene, water, alcoh
Flight qualification of the product	Letter "O1", flight use
Possibility to adapt the product to customer requirements	Yes
Internal Diameter	2.2 mm
Water Flow Rate / Hydraulic Resistance	80 g/s/not over 0.343 MPa

price on request

Glavkosmos

Solenoid Valves RT 200-00-02-03

The Solenoid Valve RT 200-00-02-03 is a single-stage, multi-starting, normally closed valve with a Teflon seal, designed for remote flow control of liquid and gaseous working media

Purpose	Flow remote control of liquid and gaseous working media (NTO, UDMH, kerosene, water, alcoh
Flight qualification of the product	Letter "O1", flight use
Possibility to adapt the product to customer requirements	Yes
Internal Diameter	1.8 mm
Water Flow Rate / Hydraulic Resistance	22 g/s/not over 0.147 MPa

price on request

Glavkosmos

Station Keeping Thruster Unit Based on Modified Thermocatalytic Thrusters

A thermocatalytic thruster unit designed for spacecraft station keeping, utilizing hydrazine propellant and featuring redundant components for reliability.

Purpose	Spacecraft station keeping
Year of release	2009
Guaranteed service life	10 years
Estimated production / delivery time	12 months
Flight qualification of the product	No

price on request

Glavkosmos

Station Keeping Thruster Unit Based on Thermocatalytic Thrusters

A thermocatalytic thruster unit designed for spacecraft station keeping, utilizing hydrazine propellant and featuring main and redundant thrusters, heaters, and temperature sensors

Purpose	Spacecraft station keeping.
Year of release	1999
Guaranteed service life	7 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes

price on request