Chemical Propulsion

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

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)

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)

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

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

Applied Ion Systems

AIS-SWAG1-QUAD

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

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

$12 500

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

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

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

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

Benchmark Space Systems

Halcyon

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

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

price on requestdatasheet

Benchmark Space Systems

Peregrine Bipropellant Thruster System

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

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

price on request

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

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

1 N GP Thruster

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

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

price on request

Bradford Space

1 N HPGP Thruster

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

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

price on request

Bradford Space

100 mN HPGP Thruster

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

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

price on request

Bradford Space

200 N HPGP RCS Thruster

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

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

price on request

Bradford Space

200 N HPGP Thruster

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

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

price on request

Bradford Space

22 N HPGP Thruster

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

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

price on request

Bradford Space

5 N HPGP Thruster

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

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

price on request

Bradford Space

HPGP 200N Thruster — High-Performance Green Propellant Propulsion

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

price on request

Bradford Space

HPGP High Performance Green Propellant Thruster

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

price on request

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

Busek Co.

BGT-X5

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

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

price on requestdatasheet

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 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

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

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

Dawn Aerospace

B20 Thruster

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

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

price on request

Dawn Aerospace

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

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

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

price on requestdatasheet

Dawn Aerospace

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

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

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

price on requestdatasheet

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

Deep Space Industries (Bradford Space)

Bradford ECAPS HPGP Thruster

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

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

price on request

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

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

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

Digital Solid State Propulsion

AF-M315E (ASCENT)

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

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

$3 850datasheet

Digital Solid State Propulsion

AF-M315E (ASCENT) Green Monopropellant

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

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

$385 010datasheet

Digital Solid State Propulsion

GEM (Green Electric Monopropellant)

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

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

price on requestdatasheet

Digital Solid State Propulsion

GEM3 Green Electric Monopropellant

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

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

$100 100datasheet

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

DREAM Aerospace

ATOM

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

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

price on request

DREAM Aerospace

ATOM Monopropellant Thruster

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

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

price on request

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

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

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

Glavkosmos

3TU Thruster Unit

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

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

price on request

Glavkosmos

Attitude Control Thruster Unit Based on Modified Thermocatalytic Low Thrusters

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

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

price on request

Glavkosmos

Attitude Control Thruster Unit Based on Thermocatalytic Low Thrusters

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

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

price on request

Glavkosmos

Bipropellant Tank with Stiff-Plastic Separation Devices (Diaphragms)

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

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

price on request

Glavkosmos

Bipropellant Thruster

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

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

price on request

Glavkosmos

Bipropellant Thruster 11d

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

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

price on request

Glavkosmos

Bipropellant Thruster 17D

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

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

price on request

Glavkosmos

Modified Thermocatalytic Low Thruster

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

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

price on request

Glavkosmos

Modified Thermocatalytic Thrusters

Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid va

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

price on request

Glavkosmos

Monopropellant Tank with Stiff-Plastic Separation Device (Diaphragm)

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

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

price on request

Glavkosmos

MULTI-LAYER BELLOWS

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

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

price on request

Glavkosmos

Pressure Stabilization Unit

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

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

price on request

Glavkosmos

RD-120MS

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

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

price on request

Glavkosmos

RD-171 M

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

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

price on request

Glavkosmos

RD-180

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

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

price on request

Glavkosmos

RD-181

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

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

price on request

Glavkosmos

Station Keeping Thruster Unit Based on Modified Thermocatalytic Thrusters

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

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

price on request

Glavkosmos

Station Keeping Thruster Unit Based on Thermocatalytic Thrusters

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

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

price on request

Glavkosmos

Thermocatalytic Low Thruster

A hydrazine thermocatalytic low-thrust engine used for spacecraft orientation, attitude control, and station keeping.

Purpose	Spacecraft orientation, attitude control, and station keeping
Year of release	1994
Guaranteed service life (years)	10.5
Estimated production / delivery time (months)	10
Flight qualification of the product	Yes

price on request

Glavkosmos

Thermocatalytic Thrusters

Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid va

Thrust	5.6 … 1.0 (7.0 … 4,0) N
Propellant inlet pressure	(883..204)/ (1030..780) kPa
Specific impulse in a continuous mode of operation	(220..214) s
Specific impulse in a pulse mode of operation	≥170 s
Life in terms of propellant throughput, kg	20(150) kg

price on request

Glavkosmos

TU1 Thruster Unit Based on Modified Thermocatalytic Low Thruster

The TU1 Thruster Unit is a thermocatalytic low thruster designed for spacecraft orientation and attitude control, using hydrazine as propellant.

Year of release	2013
Guaranteed service life	5 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes
Possibility to adapt the product to customer requirements	Yes

price on request

Glavkosmos

TU3 Truster Unit Based on Modified Thermocatalytic Low Thrusters

The TU3 Truster Unit is a propulsion system designed for spacecraft orientation and attitude control, utilizing three modified thermocatalytic low thrusters and hydrazine propellan

Purpose	Spacecraft orientation and attitude control.
Year of release	2013
Guaranteed service life	5 years
Estimated production / delivery time	12 months
Flight qualification of the product	Yes

price on request

Glavkosmos

Working Medium Tank MVSK

The Working Medium Tank MVSK is a monopropellant propulsion system designed for spacecraft, storing and feeding hydrazine to liquid propellant thrusters.

Purpose	Monopropellant propulsion system for spacecraft
Flight qualification of the product	Letter "O", flight use
Possibility to adapt the product to customer requirements	Yes
Propellant	Hydrazine
Operating Pressure, not over	1.32 MPa

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

Russian satellite manufacturer in Zheleznogorsk, Siberia; GLONASS-K/M navigation, Express GEO comms, Luch data relay, and Yamal satellites; 1,400+ spacecraft built.

ISS Reshetnev

Attitude Control Propulsion Unit

The Attitude Control Propulsion Unit (ACPU) developed by ISS Reshetnev provides thruster-based attitude control and fine station-keeping for geostationary and medium-orbit satellit

price on request

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

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	7W 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

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	300N

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 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

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

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

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

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

price on request

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

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

price on requestdatasheet

European propulsion specialist building aerospike, in-space and staged-combustion rocket engines, including the world's first methalox aerospike engine.

Pangea Aerospace

Arcos

Pangea's flagship methalox aerospike engine platform (second stage: 750 kN) -- the world's first tested LOX/methane aerospike, offering altitude-compensating efficiency for launche

Propellants	LOX / Methane (methalox)
Thrust (second stage)	750 kN
Cycle	Gas generator (open cycle)
Nozzle	Aerospike -- altitude-compensating, efficient from sea level to vacuum
Combustion chamber	Modular, deep-throttleable, bi-material additively manufactured

price on request

Pangea Aerospace

Cryox

30 kN LOX/methane kick-stage engine with an electric-pump feed cycle, deep throttling (100% to 10%) and multiple restart capability for orbital insertion and precision docking.

Propellants	LOX / Methane (methalox)
Thrust	30 kN
Cycle	Advanced electric-pump (e-pump) cycle
Throttle range	100% down to 10%
Restart capability	Multiple restarts, reignitable

price on request

Pangea Aerospace

Kronos

Full-flow staged combustion methalox engine in development, intended to be Europe's first FFSC engine and the most powerful ever conceived on the continent, built for heavy and sup

Propellants	LOX / Methane (methalox)
Cycle	Full-Flow Staged Combustion (FFSC)
Thrust	In development; ESA study targets over 2,000 kN (2 MN)
Thrust class	Over 100 tons (approx. 1,000 kN) for heavy-lift/deep-space missions
Manufacturing	Bi-material additive manufacturing

price on request

Pangea Aerospace

Nereus 20 B

Bipropellant in-space thruster (20 N) balancing efficiency and versatility with green, storable propellants, capable of operating in monopropellant mode.

Propellant type	Bipropellant (also operable in monopropellant mode)
Propellants	H2O2 / Jet A
Thrust	20 N
Manufacturing process	LPBF-qualified additive manufacturing, millimetric tolerances
Compliance	REACH compliant, ITAR-free

price on request

Pangea Aerospace

Nereus 20 M

Monopropellant in-space thruster (5-22 N) running on green, storable hydrogen peroxide (H2O2) for satellite station-keeping, attitude control and controlled deorbiting.

Propellant type	Monopropellant
Propellant	H2O2 (hydrogen peroxide)
Thrust	5-22 N
Manufacturing process	LPBF additive manufacturing, millimetric tolerances
Compliance	REACH compliant, ITAR-free

price on request

Pangea Aerospace

Nereus 200

Higher-thrust extension of the Nereus in-space bipropellant family (100-240 N), aimed at orbital transfer vehicles, lunar landers and high-velocity defense platforms. Coming soon.

Propellant type	Bipropellant
Propellants	H2O2 / Jet A
Thrust	100-240 N
Status	Coming soon
Compliance	REACH compliant, ITAR-free

price on request

American propulsion company developing high-performance green propellant rocket engines for commercial and government launch vehicles and spacecraft.

Parabilis Space Technologies

H2O2/HTPB Hybrid Upper Stage

High-performance hydrogen peroxide / HTPB fueled hybrid rocket upper stage for small launch vehicles.

Propellants	H2O2 (hydrogen peroxide) / HTPB
Application	Small launch vehicle upper stage
Ignition	Custom pyrotechnic or spark ignition hardware
Throttle	Variable-throttle demonstrated
TVC	Liquid injection thrust vector control (LITVC)

price on request

Parabilis Space Technologies

LOx/Methane RCS Thruster

Monolithic metallic additively manufactured liquid oxygen / methane reaction control system (RCS) thruster.

Propellants	LOx (liquid oxygen) / CH4 (methane)
Application	Reaction control system (RCS)
Manufacturing	Monolithic metallic additive manufacturing (3D-printed)
Application target	Spacecraft attitude control, deep-space architectures

price on request

Parabilis Space Technologies

SmallSat Hybrid Propulsion Module

Custom hybrid solid-liquid propulsion system solutions for CubeSats through ESPA Grande-class satellites, designed and integrated in-house.

Satellite class	CubeSat through ESPA Grande
Technologies available	Solar electric, liquid monopropellant, liquid bipropellant, hybrid solid-liquid
Cleanroom	Class 10,000 integration and test cleanroom
Test facility	Dedicated propulsion test site, Ramona CA, up to 5,000 lbf
Delivery	Custom design, procurement, integration, testing, and post-delivery support

price on request

Ukrainian small-launch startup developing Promin 1 (Zaarbird), an ultra-light autophagic rocket that burns its own solid-fuel airframe to orbit pico- and nanosatellites.

Israeli defence company Rafael's space division; EO satellite payloads, ADCS, propulsion, and communications systems for Israel's national defence satellite and intelligence programmes.

Rafael Advanced Defense Systems - Space Division

1N Monopropellant Hydrazine Thruster

The Rafael 1N Monopropellant Hydrazine Thruster generates the required thrust for maneuvering satellites by means of a hot gas jet created by hydrazine decomposition and expansion

price on request

Rafael Advanced Defense Systems - Space Division

200N Monopropellant Hydrazine Thruster

The Rafael 200N Monopropellant Hydrazine Thruster is a high-thrust space propulsion unit designed for integration into Roll Attitude Control System (RACS) clusters for satellite la

price on request

Rafael Advanced Defense Systems - Space Division

25N Monopropellant Hydrazine Thruster

The Rafael 25N Monopropellant Hydrazine Thruster is designed for high-thrust satellite maneuvers, providing 9.5 to 28 N of steady-state thrust across its operational feed pressure

price on request

Rafael Advanced Defense Systems - Space Division

5N Monopropellant Hydrazine Thruster

The Rafael 5N Monopropellant Hydrazine Thruster is designed for satellite attitude control and orbit correction maneuvers. It produces steady-state thrust from 1.8 N at 5.5 bar to

price on request

Rafael Advanced Defense Systems - Space Division

PEPT-230 Diaphragm Propellant Tank

The PEPT-230 (Positive Expulsion Propellant Tank) is a spherical titanium propellant tank with 6 liters nominal volume designed for hydrazine monopropellant propulsion systems. Pos

price on request

Rafael Advanced Defense Systems - Space Division

PEPT-260 Diaphragm Propellant Tank

The PEPT-260 is a spherical titanium propellant tank with 9.3 liters nominal volume for hydrazine monopropellant propulsion systems. It uses an EPN-40 silica-free EPDM diaphragm fo

price on request

Rafael Advanced Defense Systems - Space Division

PEPT-420N Diaphragm Propellant Tank

The PEPT-420N is a large-volume spherical titanium propellant tank with 37.5 liters nominal volume and 30 kg maximum hydrazine capacity. It is one of Rafael’s most heritage-r

price on request

Affordable hardware development for miniaturized aerospace systems, with a proven flight-heritage track record in nanosatellite power, propulsion and RF tracking subsystems.

Stellar Exploration, Inc.

Nanosatellite Mono & Bipropellant Propulsion Thruster

Miniaturized hypergolic bipropellant thruster delivering 3 N thrust at 285 s Isp, developed for a NASA-funded deep-space nanosatellite mission.

Thrust	3 N
Specific impulse	285 sec
Propellant feed	Gear pumps for precise propellant metering, low-pressure tank design
Propellant type	Hypergolic bipropellant; monopropellant variants also available
Flight heritage	NASA CAPSTONE (12U lunar mission), EchoStar EG-3 (small-satellite delta-V record)

price on requestdatasheet

Cold gas, monopropellant, and electric (iodine) propulsion systems for small satellites, deployers, and orbital transfer vehicles.

T4i - Technology for Propulsion and Innovation

ALPHARD Monopropellant Family

Family of High Test Peroxide (HTP) monopropellant thrusters (ALPHARD-10, -10-HP, -20, -20-HP, -200) for delta-v and RCS on small satellites, deployers, and orbital transfer vehicle

Propellant (Family Overview)	HTP 90 w% (customizable up to 95 w%)
Thrust Range [N] - ALPHARD-10	5.3 – 12.7
Thrust Range [N] - ALPHARD-10-HP	5.3 – 19.7
Thrust Range [N] - ALPHARD-20	10 – 22.6
Thrust Range [N] - ALPHARD-20-HP	10 – 34

price on request

US green spacecraft propulsion manufacturer; off-the-shelf thrusters, multi-thruster modules, and complete turn-key propulsion systems using low-toxicity propellants.

Tesseract

Lyra 1

Lyra 1 is a bipropellant thruster designed for SmallSat propulsion subsystems, offered by Tesseract Space.

Name	Lyra 1
Vendor	Tesseract Space
Subsystem	Propulsion Subsystem
Component Type	Bipropellant Thruster
Form Factor	SmallSat

price on requestdatasheet

Tesseract

Rigel 500

The Rigel 500 is a bipropellant thruster offered by Tesseract Space, designed for SmallSat propulsion subsystems.

Name	Rigel 500
Vendor	Tesseract Space
Subsystem	Propulsion Subsystem
Component Type	Bipropellant Thruster
Form Factor	SmallSat

price on requestdatasheet

Polish green space propulsion company in Warsaw; hydrogen peroxide propellants and catalysts as eco-friendly hydrazine alternatives for satellite propulsion systems.

Thaliana Space

1N HTP Monopropellant Thruster

1 N monopropellant thruster running on 98% high-test peroxide, developed at Łukasiewicz - ILOT and commercially produced by Thaliana Space under license for satellite ACS and deorb

Propellant	98% HTP (monopropellant)
Nominal Thrust	1 N
Type	Catalytic monopropellant thruster
Licensor	Łukasiewicz Research Network - Institute of Aviation
License signed	February-March 2025

price on request

Thaliana Space

420N HTP Bipropellant Kick-Stage Engine

420 N-class bipropellant rocket engine using 98% hydrogen peroxide as oxidizer, developed under ESA's GRACE 1/2 programs and manufactured by Thaliana Space for MaiaSpace's Colibri

Nominal Thrust	420 N (per engine)
Oxidizer	98% hydrogen peroxide (HTP)
Type	Bipropellant liquid rocket engine
Application	Kick-stage / orbital transfer vehicle (OTV) / launcher upper stage
Heritage	ESA GRACE 1 & GRACE 2 programs, Łukasiewicz - ILOT

price on request

Thaliana Space

Green Propulsion System (4x1N HTP Monopropellant Module)

Blowdown monopropellant propulsion system using 98% HTP with four 1 N thrusters for LEO small-satellite orbital maneuvers, attitude control, and end-of-life deorbit.

Propellant	98% HTP
Wet mass	< 25 kg
Dry Mass	< 12 kg
Type	Blowdown monopropellant
Total Impulse	14000 Ns

price on request

UK electric propulsion company; Hall-effect thrusters using water vapour or gaseous oxygen; electrolysis propulsion and microwave electrothermal thrusters; green propellant alternatives.

URA Thrusters

URA ICE Thruster (Electrolysis Chip Thruster)

MEMS-manufactured propulsion system combining water electrolysis and hydrogen-oxygen catalytic combustion in a chip-based thruster, scalable from CubeSats to large satellites.

Model	ICE-10
Thrust	10 mN
Specific impulse (Isp)	310 s
Power	5 / 25-800 W
Dimensions	<4 U

price on request

US manufacturer of precision fluid control components and integrated propulsion systems for spacecraft, with 70+ years of heritage. Products include micro propulsion systems, valves, pressure regulators, and CubeSat propulsion modules.

VACCO Industries

Integrated Propulsion System (IPS)

VACCO's Integrated Propulsion System (IPS) is a complete, bolt-on propulsion module for SmallSats, providing attitude control and delta-V with a total impulse of 12,000 N-sec.

Total Impulse	12,000 N-sec
Thruster Type	1N LMP-103S green monopropellant thrusters
Number of Thrusters	Four
Net Axial Thrust	3.97N
Thruster Flight Heritage	56 units successfully flown since 2010

price on requestdatasheet

Argentine space engineering company (Buenos Aires, founded 2007) and prime contractor to CONAE for the Tronador II launch vehicle programme, satellite avionics, propulsion, and ground-segment systems.

VENG S.A.

MOTOR MT-B

The MT-B is a bipropellant liquid rocket engine with a single regeneratively cooled thrust chamber, designed for the second stage of the Tronador TII-250 launch vehicle.

USO	Segunda etapa (óptima) o clúster de primera etapa
EMPUJE EN VAC	4280 Kgf
PROPELENTES	LOX/RP1
IMPULSO ESPECÍFICO EN VAC	330 S
SISTEMA DE ALIMENTACIÓN	CICLO GENERADOR DE GASES

price on requestdatasheet

VENG S.A.

MT-B

The MT-B is a bipropellant liquid rocket engine with a single regeneratively cooled thrust chamber, designed for the second stage of the Tronador TII-250 launch vehicle.

USO	Segunda etapa (óptima) o clúster de primera etapa
EMPUJE EN VAC	4280 Kgf
PROPELENTES	LOX/RP1
IMPULSO ESPECÍFICO EN VAC	330 S
SISTEMA DE ALIMENTACIÓN	CICLO GENERADOR DE GASES

price on requestdatasheet

Yuzhnoye State Design Office (KB Pivdenne) is Ukraine's premier rocket and space engineering organization, providing full-cycle development of launch vehicles, spacecraft, and propulsion systems. Founded in 1954 and headquartered in Dnipro,

Yuzhnoye Design Bureau

Green Monopropellant Propulsion System

The Green Monopropellant Propulsion System developed by Yuzhnoye SDO is intended for generating thrust impulse bits to extend spacecraft lifetime, particularly for CubeSat-class na

Working Medium	HAN-based monopropellant
Pressurant	Isobutane
Total Thrust Impulse	0.32 kN*s
Thrust	0.153 N
Monopropellant Mass	0.15 kg

price on request