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.

Design life	10 years in LEO
Total Impulse	200 kN
Operating temperature	-30…+60 °C
Shock level	12.3 g (RMS) - 9.5 g Rms
Vibration level	20grms

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

Hall Thruster Systems

Aliena's Hall Thruster Systems are engineered as integrated, plug-and-play solutions, offering both COTS and bespoke configurations for various space missions.

Spacecraft bus input	25 - 36 V
Tcu input	25 - 36 V | 6 A (Peak)
Tcu comms	Redundant CAN bus via CSP | RS422 available (TBD)

price on request

aliena

Hall Thrusters

ALIENA offers a range of Hall Thrusters designed for various satellite classes, providing efficient and reliable propulsion solutions.

price on request

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 Flight-ready | 2nd gen qualified 2026

The most capable integrated propulsion solution for nanosatellites and microsatellites, a fully self-contained 4U system ready to integrate.

Form factor	4U
Wet mass	6 kg
System power	100 W
Specific impulse	~700 s
Total impulse	~15 kNs

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 requestdatasheet

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	500 mW
Primary capacitor bank	0.136uF
Primary bank working voltage	2 kV

$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	5 W
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	20 W
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	2.5 W
Shot lifetime (10^-2 Torr)	>300,000
Shot lifetime (10^-6 Torr)	60,000
Rep rate	Single Shot to 8 Hz

$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	5 W or 10 W Options
Min thrust	8.4uN (1 W)
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	2.5 W or 5 W 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	2.5 W or 5 W Options
Min thrust	4.2uN (<1 W)
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	10 W or 20 W Options
Min thrust	16.8uN (2 W)
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	20 W
Thrust (Beginning of Life)	128uN (at 2 Hz)
Thrust (End of Life)	32uN (at 2 Hz)
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	40 W
Thrust	256uN (at 4 Hz)
Thrust (End of Life)	64uN (at 4 Hz)
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

Astra Space

Satellite Engine

Astra's Satellite Engine offers superior fuel efficiency with a thrust range of ~18-25 mN, providing mission flexibility for various space applications.

Specific impulse	~1,300-1,400s
Thrust range	~18-25 mN
Propellant options	Xenon (Xe) or Krypton (Kr)

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

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, attitude control, deorbit
Propellant	PTFE, 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 (2)	3 Plasma Brake tethers
Launch scheduled	11 ARM thrusters
Launch scheduled (2)	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

High-Test Peroxide Systems – Halcyon

Benchmark Space Systems offers High-Test Peroxide (HTP) propulsion systems, including the Halcyon monopropellant and Halcyon Avant bipropellant thrusters, designed for high-thrust

Halcyon Monopropellant Thrust Per Thruster	1 - 10 N
Halcyon Monopropellant Specific Impulse	155 - 160 s
Halcyon Avant Bipropellant Thrust Per Thruster	20 N
Halcyon Avant Bipropellant Specific Impulse	270 - 280 s
Missions Enabled	14

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

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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

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

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

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 requestdatasheet

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	20 W

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Busek Co.

BGT-X5 Green Monopropellant Thruster

Busek's Green Monopropellant Thrusters feature a patented monolithic catalyst that is efficient yet extremely robust, with available thruster sizes ranging from 0.1N to 22N class.

System Power	20 W
Input Voltage	6-16 VDC (nominal 12 V)
Interface	RS-422
Propellant	ASCENT
Thrust	500 mN nominal

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
Supply 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
Supply 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
Supply 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	350 W
Throttle range	200 W-600W
Nominal thrust	17 mN
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	600 W
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
Supply 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 requestdatasheet

Busek Co.

Electrospray Thrusters

Enabling unique missions in space-based science, from detecting gravity waves to stabilizing large observatories, these thrusters offer precise thrust control and efficient operati

System Power	12 W - 14 W (24 W max)
Propellant	Ionic Liquid
Thrust	<1uN-150uN range per thruster
Thrust Noise	<0.2uN/rtHz
Specific Impulse	850 seconds - 2300 seconds

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Busek Co.

FalconSat-3

The FalconSat-3 features the first 3-electrode micro-pulsed plasma thruster (μPPT) in space, launched in 2007.

price on request

Busek Co.

Hall Thrusters

Busek develops leading edge electric propulsion thrusters to enable entirely new classes of spacecraft missions, balancing extraordinarily high specific impulse with excellent thru

price on request

Busek Co.

LISA Pathfinder First Flight Electrospray Thruster

Busek delivered eight electrospray thruster clusters for the NASA/ESA LISA Pathfinder mission, ST7, a technology demonstration mission to prepare for the Laser Interferometry Space

price on request

Busek Co.

RF Ion Thrusters

Extremely compact and versatile systems for spacecraft classes from small satellites to nanosatellites, featuring high performance and unprecedented efficiency at its size.

System Power	56-80 W
Thrust	Up to 1.25 mN
Specific Impulse	Up to 2300s
Delta-V	Up to 2.5 km/s (14 kg CubeSat)

price on requestdatasheet

Busek Co.

SUB-KILOWATT HALL THRUSTERS

Sized perfectly for small satellites and CubeSats, these scalable solutions offer high performance for various applications.

price on request

Busek Co.

TacSat-2

The TacSat-2 satellite, launched in 2006, featured Busek's 200W Hall Thruster, marking the first US-designed and US-built Hall thruster in space for primary propulsion.

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 (2)	6U
Form factor (3)	12U
Form factor (4)	Smallsat
Watercube propulsion unit volume	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

China Great Wall Industry Corporation (CGWIC)

Launch Vehicle Sales Agency

China Great Wall Industry Corporation's international commercial launch services using Long March vehicles for GEO, MEO, and LEO satellite deployments.

Service type	International commercial launch agency
Primary vehicles	Long March 3B (GTO), Long March 2D/2C (LEO/SSO), Long March 7
Lm-3b GTO payload	up to 5,500 kg
Missions completed	50+ international satellites
Services	Launch only, or full turnkey (satellite + launch + ground segment)

price on request

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 (0.5U)

The CubeSat High Impulse Propulsion System (CHIPS) is a compact propulsion unit designed for CubeSats, offering significant total impulse for mission maneuvers.

Total Impulse	176 N-s
Thrust	15.00 mN
Specific Impulse	67 sec
Wet Mass	1,079 g
Volume Impulse	326 N-s/liter

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

Filament pulsed plasma thruster (FPPT)

Fiber-Fed Pulsed Plasma Thruster (FPPT) provides high specific and total impulse for small satellites, available in various form factors.

Minimum specific impulse	3,500 s
Thrust vectoring	±5 degrees
Volume range	0.7 to 53 liters
Total impulse range	1,000 to 600,000 N-s
Package size for >25,000 N-s total impulse	1.7 liters

price on requestdatasheet

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 requestdatasheet

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

Monofilament Vaporization Propulsion (MVP)

The Monofilament Vaporization Propulsion (MVP) system uses 3D printer technology to provide continuous electrothermal thrust with Delrin fiber propellant.

Specific Impulse	66 s
Volume	0.93-liter
Total Impulse	265 N-s

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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

CU Aerospace

Plasma Systems Technology

CU Aerospace is developing multiple plasma-based technologies to address emerging needs in various industries, including low-temperature sterilization and plasma-assisted combustio

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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
Thrust mode	Single-pulse high-thrust, continuous, or combined
Acceleration	> 10 g
Maneuver time	< 1 sec

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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

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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

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

Hybrid Rocket Motors

DELTAV Space Technologies develops, tests, and produces hybrid rocket motors with unique internal ballistic technology, achieving solid-propellant rocket thrust levels for the firs

Thrust

1 N to 200 kN

price on request

DELTAV Space Technologies

Liquid Propulsion Systems

DELTAV Space Technologies develops single and dual liquid-fueled propulsion systems for spacecraft maneuvering and high-performance applications, utilizing green fuels for safety a

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

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 # (2)	315-50
Qty (2)	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

$3 850datasheet

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)

$100datasheet

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

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 1 N
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

ENPULSION GmbH

Micro R³

The Micro R³ is a scaled version of Enpulsion's flight-proven thruster design, making it an ideal propulsion system for small and medium-sized spacecraft.

Dynamic Thrust Range	0.5 - 1 mN
Nominal Thrust	110 W incl. neutralizer
Specific Impulse	2,700s at 1 mN
Propellant Mass	1.25 kg
Total Impulse	26 kNs at 1 mN

price on requestdatasheet

ENPULSION GmbH

Nano R³

An evolved, flight-proven system that enhances protection and reliability, the Nano R³ delivers dynamic ISP ideal for nanosatellites and CubeSat missions.

price on request

ENPULSION GmbH

Nexus

The Nexus propulsion system is designed for spacecraft ranging from 150-500kg, offering high power propulsion with unrivaled impulse density.

price on request

ENPULSION GmbH

Scalable Propulsion Portfolio

Enpulsion offers a scalable electric propulsion portfolio featuring modular, plug-and-play FEEP-based units designed to streamline integration and accelerate mission timelines for

price on request

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

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
Design life	5 years In-Orbit

price on request

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

Froberg Aerospace

Multimode Integrated Monopropellant Electrospray (MIME) Thruster

The Multimode Integrated Monopropellant Electrospray (MIME) Thruster is a propulsion system for small satellites that can operate in either a high-thrust chemical mode or a high-sp

price on request

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
Pressurization hardware	None required
TRL	7-8
Gen-01 launch	25 May 2022, SpaceX Transporter-5 (D-Orbit ION platform)

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

South Korean aerospace and defense company developing rocket engines for the KSLV-II (Nuri) launcher and next-generation Korean launch vehicles.

Hanwha Aerospace

KRE-075 Rocket Engine — Nuri/KSLV-II First Stage Propulsion by Hanwha

Hanwha Aerospace is a South Korean defense and aerospace conglomerate providing engine systems for Korea’s Nuri (KSLV-II) orbital launch vehicle. Hanwha Aerospace designed an

price on request

Hanwha Aerospace

Nuri (KSLV-II) Engine System

Hanwha Aerospace manufactures the rocket engines for Nuri (KSLV-II), South Korea’s first domestically developed orbital launch vehicle. Hanwha produced the 75-ton-force liqui

price on request

Australian aerospace startup developing the HL-1 — claimed world's most efficient rocket engine — powered by green hydrogen, 3D-printed metal, 25% better Isp, fully reusable, and scalable from CubeSat to lunar lander.

Herik Labs

Herik Labs HL-1 Green Hydrogen Rocket Engine

Australian green hydrogen rocket engine — 25% higher Isp than alternatives, metal 3D-printed with 85% fewer parts, fully reusable, no battery required in engine cycle. Scalable fro

Propellant	Green hydrogen
Emissions	Zero greenhouse gas during operation
Manufacturing	Metal 3D printing
Part count reduction	Up to 85% fewer parts vs conventional engines
Specific impulse improvement	25% greater than alternative engines

price on request

Beijing satellite constellation company partnered with Blue Arrow Aerospace; develops communications, remote sensing, and science satellites plus in-house Jinwu propulsion, Chiyu power, and Baize electronics subsystems.

Hongqing Technology (鸿擎科技)

Jinwu Electric Propulsion System

The Jinwu Electric Propulsion System is Hongqing Technology next-generation argon-fueled electric propulsion platform, developed entirely in-house for commercial LEO satellite appl

Propellant	Argon (Ar)
In-orbit ignition cycles	4,089 (verified as of June 8, 2026)
Ignition success rate	100%
Cumulative orbital maneuver altitude	1,434 km
Supply module - pressure regulation ratio	>300:1

price on request

Hongqing Technology (鸿擎科技)

Next-Generation Argon Propellant Electric Propulsion System

Hongqing Technology's next-generation electric propulsion system utilizes argon propellant, designed for low-cost and high-reliability satellite operations through iterative innova

price on request

Howe Industries is a Scottsdale, Arizona propulsion startup developing advanced space technologies including ThermaSat water-propellant electrothermal CubeSat thrusters, nuclear pulsed plasma rockets, and orbital robotics, backed by NASA NI

Howe Industries

Pulsed Plasma Rocket (PPR)

NASA NIAC-funded nuclear pulsed-plasma propulsion concept aiming to cut crewed Mars transit time to about two months — 100,000 N thrust, 5,000 s specific impulse, 282 MW power.

Thrust	100,000 N (100 kN)
Specific impulse	5,000 s
Reactor power	282 MW
Spacecraft total mass	80,000 kg
Payload capacity	18,500 kg

price on request

Howe Industries

SEPTIR

Radioisotope-powered electric thruster delivering 3,048 s specific impulse at only 3 W power draw, targeting small satellite and deep space platforms that require long-duration, ne

Specific impulse	3,048 s
Power draw	3 W
Thrust	0.295 mN
System mass	10 kg
Propulsion type	Electric (radioisotope-powered ion)

price on request

Howe Industries

SPRINTR

Nuclear thermal rocket engine achieving 843 s specific impulse at 9,930 N thrust and 40 MW reactor power, using a scored plate reactor design with liquid hydrogen as propellant.

Specific impulse	843 s
Thrust	9,930 N
Reactor power	40 MW
Core mass	2,730 kg
Propellant	Liquid hydrogen

price on request

Howe Industries

ThermaSat

Solar thermal CubeSat propulsion system using water as a non-toxic green propellant, delivering resistojet-heated steam thrust for 3U-12U platforms at minimum 8 W input power. NSF

Propellant	Water (H2O)
Propulsion type	Solar thermal resistojet (electrothermal)
Minimum input power	8 W
Target platform	CubeSat 3U to 12U
Propellant storage	Solid or liquid (ambient pressure)

price on request

Spanish NewSpace company delivering satellite IoT connectivity, in-orbit testing, and turn-key space missions from Madrid.

Hydra Space

Hydra Space Water-Based Propulsion System

Green water-electrolysis propulsion for PocketQube and CubeSat-class satellites — non-toxic, non-pressurized propellant, solar-powered electrolysis, enabling station-keeping, phasi

Propellant	Water (H₂O)
Propulsion principle	Electrolysis (hydrogen/oxygen generation and expulsion)
Propellant safety classification	Green / non-toxic / non-pressurized
Power source	Onboard solar panels
Target platform	PocketQube 2P (5 × 5 × 10 cm, ~400 g) and CubeSats

price on request

HyImpulse Technologies develops and manufactures hybrid rocket-powered launch vehicles and in-space mobility solutions, offering launch, satellite-as-a-service, and space-data-as-a-service.

HyImpulse Technologies

Hybrid Propulsion Systems

HyImpulse's hybrid motor family powers suborbital and orbital vehicles with lightweight composite casings, thrust vector control, and modular interfaces, providing liquid-like perf

Thrust (SL1 orbital launcher)	90 kN
Thrust (SR75 sounding rocket)	75 kN
Thrust (scalable architecture)	10 kN
Propellant	Nitrous oxide hybrid
Casing	Full composite

price on request

HyImpulse Technologies

SR75 Hybrid Sounding Rocket

HyImpulse Technologies' SR75 — Germany's first privately-operated hybrid-propulsion sounding rocket, tested to over 100 km altitude from Australia.

Propulsion type	Hybrid (N2O oxidizer / paraffin wax fuel)
Engine	Bimodal Hybrid Engine (BHE)
Apogee	>100 km (above Kármán line)
Launch site	Koonibba Test Range, South Australia (Southern Launch)
First launch	2023 (first German private hybrid rocket to reach space)

price on request

South Africa-based space hardware company developing the Lumen thermal vacuum testing system and providing TVAC test services for the aerospace industry.

IHI Aerospace Co., Ltd. is a Japanese aerospace company, a subsidiary of IHI Corporation, primarily known as Japan's leading solid rocket motor manufacturer and key JAXA launch vehicle supplier.

IHI Aerospace

IHI Aerospace Spacecraft Propulsion Products

IHI Aerospace's full line of spacecraft and launch vehicle propulsion hardware, including monopropellant, bipropellant, cold-gas and electric (Hall) propulsion systems, thrusters,

Bipropellant systems - unar-a	Launch Year: cancelled; Orbit: Lunar orbit; Propellant Load: N2H4 143 kg, NTO 49 kg; Thrus
Bipropellant systems - ets-vi	Launch Year: 1994; Orbit: GEO; Propellant Load: N2H4 910 kg, NTO 825 kg; Thruster Configur
Bipropellant systems - j-i eve	Launch Year: 1996; Orbit: Launcher; Propellant Load: N2H4 126 kg, NTO 120 kg; Thruster Con
Bipropellant systems - comets	Launch Year: 1998; Orbit: GEO; Propellant Load: N2H4 1030 kg, MON3 840 kg; Thruster Config
Bipropellant systems - drts	Launch Year: 2002; Orbit: GEO; Propellant Load: N2H4 973 kg, MON3 641 kg; Thruster Configu

price on request

IHI Aerospace

Spacecraft Propulsion Products

IHI Aerospace's family of monopropellant, bipropellant, cold-gas and electric (Hall-effect) propulsion systems, thrusters and propellant tanks for satellites, transfer vehicles and

Bipropellant system – unar-a	Launch: cancelled; Orbit: Lunar orbit; Propellant load: N2H4 143 kg, NTO 49 kg; Thrusters:
Bipropellant system – ets-vi	Launch: 1994; Orbit: GEO; Propellant load: N2H4 910 kg, NTO 825 kg; Thrusters: 1700N main
Bipropellant system – j-i eve	Launch: 1996; Orbit: Launcher; Propellant load: N2H4 126 kg, NTO 120 kg; Thrusters: 3600N
Bipropellant system – comets	Launch: 1998; Orbit: GEO; Propellant load: N2H4 1030 kg, MON3 840 kg; Thrusters: 1700N mai
Bipropellant system – drts	Launch: 2002; Orbit: GEO; Propellant load: N2H4 973 kg, MON3 641 kg; Thrusters: 500N LAE,

price on request

IHI Aerospace

Spacecraft Propulsion Systems

IHI Aerospace's spacecraft propulsion product line, encompassing bipropellant, monopropellant, cold-gas and electric propulsion systems, thrusters, tanks and launch vehicle RCS, in

Bipropellant system - unar-a	Launch: cancelled; Orbit: Lunar orbit; Propellant Load: N2H4 143 kg, NTO 49 kg; Thrusters:
Bipropellant system - ets-vi	Launch: 1994; Orbit: GEO; Propellant Load: N2H4 910 kg, NTO 825 kg; Thrusters: 1700N main
Bipropellant system - j-i eve	Launch: 1996; Orbit: Launcher; Propellant Load: N2H4 126 kg, NTO 120 kg; Thrusters: 3600N
Bipropellant system - comets	Launch: 1998; Orbit: GEO; Propellant Load: N2H4 1030 kg, MON3 840 kg; Thrusters: 1700N mai
Bipropellant system - drts	Launch: 2002; Orbit: GEO; Propellant Load: N2H4 973 kg, MON3 641 kg; Thrusters: 500N LAE,

price on request

Indian startup developing in-orbit servicing, satellite life extension, and green propulsion; $5.6M seed funded (2025).

Inspecity Space Laboratories

GITA | Green Impulse Transmitter

GITA is an eco-friendly propulsion system designed for satellite servicing, utilizing refuellable and easy-to-source propellants to provide high thrust and impulse with instant res

Propellants	Refuellable, easy to source
Thrust	High
Impulse	Higher
Response capabilities	Instant

price on request

French startup developing ionic liquid electrospray thrusters for CubeSat and small satellite on-orbit propulsion; founded 2021.

Isar Aerospace designs and manufactures the 'Spectrum' two-stage launch vehicle for small and medium satellites and constellations, providing launch services to global customers.

Isar Aerospace

Aquila Engine

Isar Aerospace's LOX/propane regeneratively-cooled rocket engine family powering the Spectrum launch vehicle first and second stages.

Propellants	LOX/Propane (LPG)
Thrust (sea-level)	~25 kN per engine
Configuration	9× (first stage), 1× vacuum variant (second stage)
Cooling	Regenerative
Propellant feed	Turbopump-fed

price on request

Green in-space propulsion systems for CubeSats to large spacecraft, based on 10+ years of DLR R&D.

ISPTech

HIP_11 Propulsion System

Advanced green hypergolic H2O2 + ionic liquid multi-mode propulsion, up to 310 s Isp, 20-200 N.

Propellant	H2O2 (hydrogen peroxide) + ionic liquid fuel
Specific impulse (vacuum)	Up to 310 s
Propellant storage density (H2O2)	Up to 1,440 kg/m3
Propellant storage density (fuel)	Up to 1,100 kg/m3
Thrust variants	20 N and 200 N

price on request

ISPTech

HyNOx 4U CubeSat Propulsion Module

The HyNOx 4U CubeSat Propulsion Module is an integrated propulsion system for CubeSats, featuring a HyNOx-1 thruster and cold/warm gas thrusters, designed for significant deltaV an

Included hardware	1x HyNOx-1 (0.5-2 N, Isp > 260 s)
Included hardware (2)	4x Cold / Warm Gas Thrusters
Status	Available now
Capabiltites	> 4,000 Ns impulse (for standard length)
Capabiltites (2)	0.5-2 N thrust for rapid orbit changes

price on request

ISPTech

HyNOx Propulsion Systems

A customizable propulsion system family built around ISPTech's HyNOx thrusters, tanks and a proprietary control unit, tailored to individual spacecraft missions.

Included hardware	HyNOx thrusters, Propellant tanks, Feed system with sensors, Pressure relief components, F
Status	Demonstrator under testing; Customer projects ongoing
Capabilities	Thruster acceptance testing and derivation of performance models; Propulsion system integr
Impulse class	CubeSat Propulsion Systems up to 5,000 Ns; Customized Propulsion Systems starting from 5,0
Thrust classes	HyNOx-200 Thruster (50-400 N); HyNOx-22 Thruster (11-44 N); HyNOx-5 Thruster (2.5-10 N); H

price on request

IVO Limited (Infinity Voltaic Orbits) is a US-based space propulsion company developing the Ionic Field Drive (IFD) — an electrically-powered thruster technology that the company claims generates thrust without propellant by manipulating el

IVO Limited

IVO Quantum Drive

Pure electric satellite thruster requiring zero propellant, based on asymmetric capacitive technology drawing on principles of Quantized Inertia.

Claimed thrust per unit	45–52 mN
Power consumption	1 W per unit
Propellant	None (zero fuel)
Mass per unit	~300 g
Scalability	Stackable modular units

price on request

Spanish space technology startup developing satellite constellation infrastructure and communications solutions.

Kreios Space

Air-Breathing Electric Propulsion (ABEP) Thruster

Electric thruster ingesting residual atmospheric particles at Very Low Earth Orbit and converting them to plasma for continuous thrust — no onboard propellant tank required.

Satellite platform lifetime	>7 years
Operating altitude	Can extend below 200 km
Propellant	None required — ingests atmospheric gas
Development generations	K-1 (2021), K-2 (2023), K-3 (2024)

price on request

Kreios Space

Kreios Space VLEO Propulsion System

A proprietary air-breathing, solar-powered electric propulsion system that enables satellites to sustain long-duration operations in Very Low Earth Orbit without onboard fuel tanks

Target orbit	~200 km (VLEO)
Image resolution improvement	Up to 3x higher than conventional LEO
Optical resolution target	Sub-10 cm
Data rate improvement	7x higher
Cost reduction claimed	>50%

price on request

L.Garde designs, develops, and manufactures inflatable and deployable structures for space and terrestrial applications, including solar sails and advanced observation structures.

L.Garde Inc

L.Garde Solar Sails

L.Garde solar sails utilize a unique “stripe net” architecture for space propulsion, offering capabilities like debris removal, satellite de-orbiting, and deep space travel.

Ground-deployed sail sizes	83 sq m and 318 sq m
Sunjammer solar sail	1200 sq m total (300 sq m quadrant deployed)
Deployment mechanism	4 independently-controlled sub-Tg conically-deployed composite booms
Applications	Debris removal, de-orbiting, pseudo-Lagrange points, pole-sitter satellites, deep-space pr

price on request

Lanzo Batteries designs and manufactures lithium-ion battery packs for space energy storage, serving large satellites, small satellites, and CubeSats.

Lanzo Batteries

AEPS Advanced Electric Propulsion System — Hall-Effect Ion Thruster for NASA Gateway

L3Harris Technologies is a US defense technology company providing space systems, communication electronics, and space propulsion. L3Harris (formed by the 2019 merger of L3 Technol

price on request

Latitude designs and manufactures a multi-configurable launcher in France for dedicated SmallSat launch services, offering frequent and affordable access to orbit.

VAST subsidiary developing the E-2 LOX/kerosene staged combustion rocket engine, designed for sale to small satellite launch vehicle developers.

Launcher (VAST subsidiary)

E-2 liquid rocket engine

The E-2 is a LOX/Kerosene oxidizer-rich staged combustion engine designed for small launch vehicles, aiming to be the most efficient in its class.

Product	Orbiter orbital transfer vehicle
Parent	VAST
Service	Last-mile satellite delivery, hosted payloads

price on request

Launcher (VAST subsidiary)

Launcher E-2 Liquid Rocket Engine

Launcher's E-2 liquid oxygen/RP-1 rocket engine — a 22,000 lbf thrust engine developed using advanced manufacturing for Launcher Light small orbital rocket (now part of VAST).

Engine	E-2 — LOX/RP-1 (liquid oxygen/kerosene), expander-bleed cycle
Thrust	22,000 lbf (sea level)
Manufacturing	3D-printed chamber and nozzle components
Test site	NASA Stennis Space Center + Launcher's own facility
Parent	VAST (acquired Launcher 2023; Haven-1 space station operator)

price on request

Japanese startup developing safe high-thrust hybrid propulsion systems using plastic as rocket fuel, founded by Hokkaido University hybrid propulsion experts.

Letara

DARUMA Micro Hybrid Propulsion Unit

Modular hybrid propulsion unit using solid HDPE fuel and N2O oxidizer for last-mile orbital maneuvers of small satellites — accelerates a 10kg payload to 1,100 m/s, 3D-printed manu

Wet mass	30 kg
Performance (10kg payload)	Accelerates to 1,100 m/s
Performance (100kg payload)	Accelerates to 400 m/s
Performance (300kg payload)	Accelerates to 130 m/s
Fuel	HDPE (high-density polyethylene)

price on request

Liftero designs and manufactures mission-configured green chemical propulsion systems for satellites, with their BOOSTER product line proven in space.

Liftero

BOOSTER

Mission-configured, high-thrust green chemical propulsion system for satellites, enabling fast orbit transfer, collision avoidance, in-orbit servicing, and re-entry missions.

Orbit transfer time	1 to 3 days
Power consumption	7 W for 1N thrust
Propellants	N₂O + C₂H6 (self-pressurizing, green chemical propellant)
Flight heritage	RED5 mission, launched on SpaceX Transporter-13, March 2025 — first Polish propulsion syst
Development timeline	Concept to flight in 15 months

price on request

British in-space propulsion company developing compact, high-thrust electric plasma thrusters using solid metal propellant for satellites and spacecraft.

Magdrive

Paladin

Paladin is a pulsed plasma propulsion system that uses solid metal propellants to generate high-velocity plasma for satellite thrust.

Thrust	1 mN
Thrust (2)	15 mN
Thrust (3)	40 mN
Thrust (4)	70 mN
Thrust (5)	150 mN

price on requestdatasheet

Magdrive

Rogue

The Magdrive Rogue is an integrated electric propulsion system for 2U CubeSats, utilizing a metal propellant and pulsed power to generate high thrust.

Integrated system fits inside	single 2U cubesat
Dry mass (including propellant, onboard processor, energy storage, and plasma injector)	2.5 kg
Pulsed power system (pps) delivers	multi-kA, MW class electrical current pulse
Directional thrust vectoring	up to 10˚
Power	2 – 100 W

price on requestdatasheet

Magdrive

Warlock

The Magdrive Warlock is a compact electric propulsion system for CubeSats, utilizing a metal propellant and pulsed power to generate high thrust.

Integrated system size	2U cubesat
Dry mass (including propellant, onboard processor, energy storage, and plasma injector)	2.5 kg
Thrust vectoring	up to 10˚
Power	2 – 100 W
Thrust	0.1 – 10 N

price on requestdatasheet

Indian deep-tech startup developing green hydrogen peroxide propulsion systems for small satellites, offering safe, non-toxic thrusters and propellant management solutions for LEO missions.

Manastu Space

GP-LAM

GP-LAM is a compact, modular, and safe 300 N green thruster designed for upper stages of Launch Vehicles, Orbital Transfer Vehicles (OTVs), and GEO spacecraft, utilizing non-toxic

Thruster type	300 N thruster
Propellant	non-toxic MS289 green propellant
Features	Compact, modular and safe
Thermal management	Controlled Thermal Stress
Thrust	300 N

price on request

Manastu Space

GP-LAM Liquid Apogee Module

300N modular green propulsion Liquid Apogee Module for launch vehicle upper stages, OTVs, and GEO spacecraft — multi-restart apogee raise, plane change, and compliant deorbit.

Spacecraft type	OTVs, launch vehicle upper stage, GEO stationary satellite
Nominal thrust	300 N (BOL)
Specific impulse	250 s (BOL)
Total impulse	150,000 Ns
Max continuous firing time	450 s

price on request

Manastu Space

I-Booster

I-Booster is a modular, dynamic green propulsion system with customizable thrust capacity for maneuvering 100–500 kg satellites in Low Earth Orbit, including debris collision avoid

Configuration	Modular/Adaptable
Thrust	4 x 1 N
Total impulse	20,000 N-s
Target satellite mass	100-500 Kg

price on request

Manastu Space

I-Booster Green Propulsion System

Green chemical propulsion system with 4x1N thrusters for 100-500kg satellites — hydrazine-free alternative delivered to India's DRDO for satellite maneuvering, December 2024.

Satellite weight	100-500 kg
Nominal thrust	0.5 N, 1 N
Specific impulse	~250 s (BOL)
Total impulse	20,000 N-s
Max continuous firing time	1000 s

price on request

Memetis GmbH designs and manufactures ultracompact microvalves and highly integrated microfluidic systems for space, life science, and medical technology applications.

Memetis

memetis Microvalves and Microfluidic Systems

Ultra-compact microvalves and highly integrated microfluidic systems from memetis, built on a patented shape-memory-alloy actuator technology, offering high packing density and low

Passive force	8 N
Stroke	0.4 mm
Mechanical interface	M2 internal thread
Width	9 mm
Max stroke (product line)	Up to 2 mm

price on request

Micro Aerospace Solutions, Inc. is a Melbourne, Florida-based small business specializing in thruster design, propulsion systems, ADCS, command and data handling, and space systems engineering for small spacecraft and nanosatellites.

Micro Aerospace Solutions

Micro-A Thrusters

Micro-A offers a range of monopropellant microthrusters from 0.005 N to 22 N, utilizing propellants like hydrogen peroxide, hydrazine, Tridyne gas, and cold gas, alongside custom p

Model	M005HP
Thrust	0.005 N
ISP (sec.)	100
Inlet pressure	350000 Pa
Minimum impulse bit (N-sec)	1.2x10^-4

price on request

Microspace Rapid Pte Ltd is a creative space engineering company that designs, builds and flies nanosatellites and proprietary space subsystems, including micropropulsion, optical imaging payloads, antennas and power systems.

Microspace Rapid

Micropropulsion

Micropropulsion is a system of micromachined microthrusters embedded in modular miniaturized modules designed for nanosatellites.

Type	Micromachined microthrusters
Integration	Embedded in modular miniaturized modules
Arrangement	Can be arranged in any corner of a nanosatellite

price on request

Microspace Rapid

Nanosatellite Micropropulsion System

The Nanosatellite Micropropulsion System is a MEMS-based micropropulsion solution for CubeSats (1kg) up to small microsatellites (100kg), offering 3-axis stabilization.

Manufacturer

MicroSpace

price on request

RocketStar is a U.S. aerospace technology company developing reusable aerospike rocket engines, water-fueled and fusion-enhanced electric propulsion for spacecraft, and a suite of digital signal processing (DSP) software for secure communic

Miles Space / RocketStar

FireStar Foundation Drive

Water-fueled pulsed plasma electric thruster in a 1U form factor for smallsat orbit raising, phasing, de-orbit and attitude control.

Propellant	H2O (filled as liquid; liquid or solid during storage/use)
Envelope	95 x 95 x 95 mm (1U with 5 mm margin)
Wet mass	980 grams
Propellant load	250 grams of liquid, pure water
System power	6 Watts (typical, all thrusters active)

price on requestdatasheet

Miles Space / RocketStar

FireStar Fusion Drive

Fusion-enhanced evolution of the FireStar water-fueled pulsed plasma thruster, delivering roughly 50% more thrust via aneutronic boron fusion.

Base thruster	FireStar Foundation Drive (water-fueled pulsed plasma)
Fusion fuel additive	Boron (aneutronic fusion in exhaust)
Thrust improvement	~50% higher than FireStar Foundation Drive
Development origin	AFWERX SBIR
Planned flight demo	Rogue Space Systems Barry-2 spacecraft, in-space testing

price on requestdatasheet

MIPRONS designs and manufactures patented water-electrolysis propulsion systems for satellites, aiming for compact, high-performance, and sustainable solutions.

MIPRONS

ALBIREO Next-Generation Propulsion System

Next-generation water-electrolysis propulsion system integrating low- and high-thrust maneuver capability in one unit — for satellites, interplanetary drones, launcher stages, and

Propulsion technology	Water electrolysis (H2-O2)
Capability	Integrated low- and high-thrust maneuvers
Applications	Satellites, interplanetary drones, launcher stages, re-entry systems, carrier vehicles
Status	Next-generation / in development

price on request

MIPRONS

ALEXIUS Water-Electrolysis Propulsion System

Compact water-electrolysis propulsion system for nanosatellites and small satellites — 1.4 kg, >2.5 N thrust, >300s Isp, 5 international patents, TRL 7 target Q3 2025.

Mass	~1.4 kg (1.3-1.5 kg)
Volume	~0.7 L (95 x 95 x 70 mm)
CUBESAT units	0.6-0.7 U (excluding fuel)
Operating pressure	30 bar (H2-O2)
Thrust	> 2.5 N (at 30 bar), up to 3 N

price on request

Vigoride orbital service vehicle — last-mile delivery, hosted payloads, in-space servicing.

Momentus Space

Microwave Electrothermal Thruster (MET)

The MET is Vigoride's primary propulsion system: a water-plasma thruster that uses solar-powered microwave energy to heat distilled water propellant and expel hot gases through a r

Propellant	Distilled water
Energy source	Solar-powered microwave
Function	Vigoride OSV primary propulsion
On-orbit status	Initial test sequence successfully completed (Vigoride-5)

price on request

Precision motion control and propulsion systems provider for space and defense applications.

Moog Space Defense Group

MONARC Monopropellant Thrusters

Moog's MONARC hydrazine monopropellant thruster family covering 1 N to 445 N thrust across six model series, with over 3,000 units delivered to commercial and government satellite

Monarc-1	Thrust 0.9–1 N; Isp 227–235 s; Mass 0.38 kg
Monarc-5	Thrust 4.5–5 N; Isp 226–230 s; Mass 0.49 kg
Monarc-22-6	Thrust 22 N; Isp 228–229.5 s; Mass 0.72 kg; 6-in nozzle
Monarc-22-12 lt/ht	Thrust 22 N; Isp 227–232 s; Mass 0.69 kg; 12-in nozzle
Monarc-90 lt	Thrust 22–90 N; Isp 232 s; Mass 1.12 kg; low-temperature catalyst

price on requestdatasheet

Electric propulsion systems for satellite mobility, deployment, and deorbiting.

Morpheus Space

GO-2 Electric Propulsion System

Modular ~1U FEEP electric propulsion unit with 40 individually controlled thrusters and solid metallic propellant, for spacecraft from 6U upwards.

Total thrust range	5 microN - 400 microN
Optimal total impulse range	12.4 kNs - 6.2 kNs
Power	7 W - 40 W
Footprint	113 x 98 mm
Dimensions	Approximately 1U modular unit

price on request

Morpheus Space

nμpro Electrospray Thruster

Morpheus Space's nμpro electrospray ion thruster — a miniaturized 'printed' propulsion unit for nanosatellites enabling formation flying and precise constellation orbit management.

Thruster type	Electrospray (ionic liquid)
Thrust range	1–100 μN per emitter array
Specific impulse	1,500–3,000 s
Manufacturing	Additive manufacturing (3D printing) — scalable production
Applications	Formation flying, constellation altitude maintenance, attitude control

price on request

University / research institute in Moscow, Russia engaged in space technology, satellite research, and small-satellite programs.

Moscow Aviation Institute

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
Design life	7 years
Lead time	12 months
Flight qualification of the product	No

price on request

Moscow Aviation Institute

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
Design life	15 years
Lead time	12 months
Flight qualification of the product	No

price on request

German aerospace components manufacturer producing satellite tanks, CFRP structures, and antenna dishes for European satellite programs.

MT Aerospace

60l S-XTA Xenon (Xe)

The 60l S-XTA Xenon (Xe) is a high-pressure vessel designed for storing Xenon, suitable for electric propulsion applications.

Capacity	60l
Propellant	Xenon (Xe)
Type	High Pressure Vessel (HPV)

price on requestdatasheet

MT Aerospace

Pressure Vessels and Cryogenic Tanks

MT Aerospace's lightweight composite overwrapped pressure vessels (COPVs) and cryogenic propellant tanks for launch vehicles and satellites — including Ariane 5/6 core stage tanks.

Products	COPVs, cryogenic tanks (LOX/LH2), solid motor casings, payload fairings
Ariane 5/6 role	EAP booster cases, LOX/LH2 tanks, payload fairing (Ariane 6), P120C motor cases
Materials	Carbon fiber composites, metallic structures
Customers	ArianeGroup, Nammo, ESA, satellite manufacturers
HQ	Augsburg, Bavaria, Germany

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MT Aerospace

Spacecraft Propulsion Tanks

MT Aerospace designs and manufactures a range of satellite propulsion tanks, including monopropellant, bipropellant, and electric propulsion tanks, at its facility in Augsburg, Ger

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Nammo is an aerospace and defense company that designs and manufactures rocket motors for military and space applications, ammunition, and shoulder-launched munitions systems.

Nammo

30kN Hybrid Engine

The 30kN Hybrid Engine is a rocket engine developed by Nammo Raufoss AS, designed for space propulsion applications.

Thrust	30,000 N in vacuum
Thrust Duration	40 seconds
Engine Mass	165 kg
Propellant Combination	87.5% H2O2, and HTPB
Specific Impulse	270 seconds, in vacuum

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Nammo

Additive Tank 100ml 1U

An additively manufactured 100ml fluid storage tank for CubeSat propulsion systems, featuring an integrated plenum tank and compact 1U x 1U x 0.2U envelope.

Fuel Volume	100 cm3
Mass	180 g
Pressure [MEOP]	10 bar
Proof Pressure	25 bar
Burst Pressure	40 bar

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Nammo

Apogee Engine Valve

The Apogee Engine Valve is a single-stage, redundant solenoid coil thruster flow control device specifically designed for propulsion system applications, compatible with various ch

Typical operating media	Typical propulsion fluids
Maximum expected operating pressure	319 psia MEOP
Surge pressure	2,031 psi for 0.2 seconds
Proof pressure	609 psi
Burst pressure	1,189 psi

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Nammo

Composite Rocket Motor Grains

Nammo Defense Systems Inc. produces composite rocket motor grains, including those for the flare A/P25S-5A Personnel Distress Signal Kit Pen Flare Emergency Military.

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Nammo

M-10 and M-100 Solid Rocket Motors

Nammo's range of solid rocket motors for sounding rockets, upper stages, and missile propulsion including the M-10 sounding rocket motor.

Products	M-10 sounding rocket motor, P120C booster segment, apogee kick motors
P120c role	First stage of Vega-C; strap-on booster for Ariane 6
M-10 altitude	Up to 200 km (two-stage sounding rocket)
Programs	Vega/Ariane 6 (P120C), PRISMA (apogee motor), sounding rockets
Country	Norway (HQ), with facilities in Finland and Germany

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Australian deep-tech company developing high-performance electric propulsion systems that use solid metal propellant (magnesium) for satellites, enabling cost-effective in-orbit maneuverability.

Neumann Space

ND-25TC Neumann Drive — Low-Power Nanosatellite Thruster

Neumann Space's ND-25TC is a 14 W, 1.9 kg solid-metal-propellant pulsed cathodic arc thruster for nanosatellites: 880+ Ns total impulse, 1,800–2,000 s Isp, sharing the same propell

Thruster type	Centre-Triggered Pulsed Cathodic Arc Thruster (CT-PCAT)
Max input power	~14 W
Total wet mass	~1.9 kg
Total impulse	≥880 Ns
Max pulse frequency	~83 mHz

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Neumann Space

ND-50 Neumann Drive — Pulsed Cathodic Arc Thruster

Neumann Space's ND-50 is a solid-metal-propellant pulsed cathodic arc thruster: 50 W max power, 1,400–2,000 s Isp, 1.4 kg total mass, 100 × 96 × 96 mm, TRL 8–9 with flight heritage

Thruster type	Centre-Triggered Pulsed Cathodic Arc Thruster (CT-PCAT)
Max input power	50 W
Specific impulse (Isp)	1,400–2,000 s (operational); up to ~14,690 s (laboratory, magnesium)
Thrust efficiency	~20 µN/W
Estimated peak thrust	~1 mN at 50 W

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Minotaur family, Pegasus XL, Antares (legacy); MLV co-development with Firefly.

Northrop Grumman Space Systems

PMD Tanks (Propellant Management Device Tanks)

A family of qualified/flight-proven propellant management device (PMD) tanks from Northrop Grumman, used to store and deliver fuel or oxidizer to spacecraft propulsion systems in m

80213-1	Total Volume: 1,232 in³ / 20.2 l; Diameter: 13.33 in ID (339 mm ID); Weight: 4.00 lbm (1.8
80277-1	Total Volume: 18,450 in³ / 302.5 l; Diameter: 32.84 in ID (834 mm ID); Weight: 32.60 lbm (
80296-1	Total Volume: 3,575 in³ / 58.6 l; Diameter: 19.03 in ID (483 mm ID); Weight: 8.00 lbm (3.6
80301-1	Total Volume: 20,900 in³ / 342.6 l; Diameter: 34.25 in ID (870 mm ID); Weight: 34.00 lbm (
80304-1	Total Volume: 3,575 in³ / 58.6 l; Diameter: 19.03 in ID (483 mm ID); Weight: 7.75 lbm (3.5

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Northrop Grumman Space Systems

Propulsion Products and Services

Northrop Grumman offers a comprehensive range of propulsion products and services, including flight-proven systems, bipropellant and monopropellant thrusters, and gel propulsion sy

Mre-0.1 thrust	0.4 N @ 350 psia; Isp 216 sec; 0.5 kg; 180x38 mm
Mre-1.0 thrust	4.4 N; Isp 220 sec; 0.5 kg; 190x38 mm
Mre-4.0 thrust	18 N @ 600 psia; Isp 217 sec; 0.5 kg; 61x206 mm
Mre-5.0 thrust	22 N @ 400 psia; Isp 232 sec; 0.8 kg; 250x38 mm
Mre-15 thrust	86 N @ 400 psia; Isp 228 sec; 1.1 kg; 119x318 mm

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Northrop Grumman Space Systems

Propulsion Tanks

Northrop Grumman offers a range of propulsion and pressurant tanks, including pressure management (PMD) tanks, diaphragm tanks, and motor cases, with six decades of on-orbit herita

Tanks flown	7,000+
On-orbit failures	0
Operational heritage	60+ years
Product family includes	PMD tanks, diaphragm tanks, pressurant tanks, motor cases

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OHB Sweden builds small satellites, AOCS and propulsion systems. It is a provider of complete space missions, satellites, and spacecraft subsystems.

OHB Sweden AB

1-20N Monopropellant System

OHB Sweden's propulsion team has developed hydrazine-based systems for European primes, offering expertise across various thrust levels and suitable products.

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OHB Sweden AB

10N Bipropellant System

OHB Sweden AB offers a 10N Bipropellant System, supported by extensive analysis capabilities and test facilities for calibration and campaign support.

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OHB Sweden AB

Cold Gas System

OHB Sweden AB provides cold gas systems using multiple gases, including miniature resistojets, with in-house characterisation and assembly services.

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OHB Sweden AB

Electric Propulsion System

OHB Sweden AB offers Electric Propulsion Systems covering various technologies like FEEP, Grid, RF, and SPT, designed with flight heritage and tailored for mission needs.

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OHB Sweden AB

EPSylon

EPSylon is an Electric Propulsion system for small satellites in a wide power and thrust range, serving both the institutional and commercial market.

Propellant	Xe
Power	250 W to 400 W per String
Supply voltage	28 V or 70 V
Thrust	8 mN to 18 mN
Specific impulse	950 s to 1390 s (Xe)

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OHB Sweden AB

Propulsion Manufacturing, Assembly, Integration and Test

OHB Sweden AB offers comprehensive services for propulsion systems, including tube etching, bending, marking, welding, cleanliness verification, and accurate pre-assembly.

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OHB Sweden AB

Propulsion Subsystem Design and Development

OHB Sweden offers comprehensive design and development services for propulsion subsystems, focusing on thorough layout modeling and tailored solutions.

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Italian electric propulsion startup developing water-propelled resistojet thruster systems for nanosatellites and microsatellites, offering a safe, low-cost, and high-performance propulsion solution.

OhmSpace

STAR-Water-micro — Water Resistojet for Microsatellites

High-thrust water resistojet propulsion for microsatellites in LEO mega-constellations — 75–150 mN thrust and 240 s Isp for collision avoidance, de-orbiting, and inclination change

Technology	High-temperature water resistojet
Target ISP	240 s
Propellant	Water (deionized/demineralized)
Power	Up to 500 W
Thrust range	75–150 mN

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OhmSpace

STAR-Water-nano — Water Resistojet for Nanosatellites

Plug-and-play water resistojet propulsion system for nanosatellites — achieves >200 s Isp in a 2U-compatible form factor. Developed under ESA GSTP contract; first launch Q2 2026

Technology	High-temperature water resistojet (2,400 K)
Target ISP	> 200 s
Propellant	Water
Form factor	From 2U
Propellant mass	From 250 g

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