Use your work email on the company domain (veng.com.ar) — we will send you a confirmation link. Other emails are reviewed manually.
VENG S.A. is an Argentine engineering and manufacturing company founded in 2007 that provides high-value technological services and development for the national space activity. It is the principal industrial contractor to CONAE, Argentina's National Space Activities Commission, and leads development of the Tronador II satellite launch vehicle programme, covering the full value chain from requirements definition through design, simulation, manufacturing, testing, qualification and vehicle integration.
The company's engineering scope spans liquid-propellant rocket engines (including the MCA2, MCA3, MES3K, MT-B, 4TR4, M150, MR500KB2 and RS-2 motor families), friction-stir-welded aluminum structural/propellant tanks and carbon-fibre composite pressure vessels (COPV) for gas storage, avionics such as the Antartix FPGA-based onboard computer and the SVD digital video system for launch vehicles, and RF/ground-segment infrastructure. VENG operates the Mission Control Centre for the SAOCOM Earth-observation satellite constellation and runs ground stations in Córdoba and Tierra del Fuego.
VENG's heritage traces through Argentina's sounding-rocket and experimental-vehicle programme: the VS-30 sounding rocket (2007), the Tronador I 1B vehicle (2008), and the VEx experimental vehicle series (VEx-1A/1B in 2014, VEx-5A in 2017) that validated navigation, guidance and control, and propulsion technologies later used on Tronador II. The company also supported the SAC-D/Aquarius (2011) and SAOCOM 1A/1B (2018/2020) satellite missions built for CONAE. VENG holds ISO 9001:2015 certification and partners with international organisations including ESA, Telespazio, MDA and satellite operators such as Satellogic and Viasat.
Pressure-fed liquid rocket engine using nitric-acid/N2O4 oxidizer, developed by VENG.
Pressure-fed liquid rocket engine using nitric-acid/N2O4 oxidizer, developed by VENG.
The 4TR4 is a pressure-fed liquid rocket engine developed by VENG using an N2O4/mixed nitric-acid propellant combination.
| Thrust (sea level) | 4,000 kgf |
|---|---|
| Propellants | N2O4 / mixed nitric acid |
| Specific Impulse (sea level) | 220 s |
| Feed System | Pressurized |
FPGA-based onboard computer/development board for nanosatellites, microsatellites and launch vehicles, built around the AMD Xilinx Artix-7 FPGA in a PCI/104-Express form factor.
FPGA-based onboard computer/development board for nanosatellites, microsatellites and launch vehicles, built around the AMD Xilinx Artix-7 FPGA in a PCI/104-Express form factor.
The Antartix v2.0 is a high-performance onboard computer and FPGA development board designed by VENG for easy integration into nanosatellites, microsatellites and launch vehicles. It is built on the AMD Xilinx Artix-7 FPGA and is optimized to run MicroBlaze and PetaLinux software. All components are rated for extended temperature range. It is available in a standard configuration (XC7A200T-1FBG484I) and a defense-qualified variant (XQ7A200T-1RB484M), with integrated GPIO, PCIe and memory interfaces in a PCI/104-Express compliant form factor.
| Form Factor | PCI/104-Express compliant |
|---|---|
| FPGA | AMD Artix-7 XC7A200T-1FBG484I |
| Memory (DDR3L) | 4Gb at 933 MHz |
| Flash Memory | 128 Mbit SPI (on-board) + 512 Mbit parallel (BPI) |
| PCIe Interface | x1 lane, Gen1.0 (2.5GT/s) |
| GPIO Pins | 11 @ 3.3V, 7 @ 1.8V |
| Power Supply | 5 VDC |
| Dimensions | 95.89 x 90.17 mm, 0.600 in height |
Pressurized and non-pressurized aluminum launch-vehicle structural/propellant tanks fabricated with friction stir welding at VENG's dedicated FSW center.
Pressurized and non-pressurized aluminum launch-vehicle structural/propellant tanks fabricated with friction stir welding at VENG's dedicated FSW center.
VENG designs, fabricates and integrates pressurized and non-pressurized aluminum structures using friction stir welding (FSW). Its most recent milestone was the design, fabrication and integration of a first-stage prototype tank for the Tronador II-250 launch vehicle, built from space-grade Aluminum 2219 and welded per American Welding Society friction-stir standards. Final-stage flight tanks are planned at 8 m (liquid oxygen) and 6 m (kerosene), doubling as both fuselage and propellant storage. The FSW center is equipped with a Nova Tech Engineering Inc. machine capable of longitudinal and circumferential, butt and lap welds on aluminum alloys.
| Prototype Length | 3.5 m |
|---|---|
| Prototype Diameter | 2.5 m |
| Wall Thickness | 3.2 mm |
| Material | Aluminum 2219 (space-grade) |
| Welding Method | Friction stir welding, AWS standard |
| FSW Machine Weld Types | Longitudinal, circumferential |
| FSW Machine Joint Types | Butt, lap |
| FSW Machine Thickness Range | 2.4-13 mm |
| FSW Machine Max Weld Length | 2,600 mm |
| FSW Machine Tool RPM | 5-2,000 |
| FSW Machine Max Load | 53,400 N |
| FSW Machine Max Torque | 450 Nm |
Family of pressure-fed small liquid rocket engines (variants A, B, C) developed by VENG.
Family of pressure-fed small liquid rocket engines (variants A, B, C) developed by VENG.
The M150 series comprises three pressure-fed liquid rocket engine variants (A, B and C) developed by VENG using an N2O4/mixed nitric-acid propellant combination, used in Argentina's experimental and launch vehicle programme.
| Thrust (sea level), A/B | 150 kgf |
|---|---|
| Thrust (sea level), C | 68 kgf |
| Propellants | N2O4 / mixed nitric acid |
| Specific Impulse (sea level), A/B | 220 s |
| Specific Impulse (sea level), C | 191 s |
| Feed System | Pressurized |
First-stage liquid rocket engine (LOX/RP-1) developed by VENG for the Tronador II launch vehicle programme.
First-stage liquid rocket engine (LOX/RP-1) developed by VENG for the Tronador II launch vehicle programme.
The MCA2 is a liquid-propellant (LOX/RP-1) rocket engine developed by VENG for the first stage of the Tronador II series of launch vehicles, as part of VENG's full-cycle propulsion development work for CONAE covering design, simulation, manufacturing, testing, qualification and vehicle integration.
| Stage | First stage |
|---|---|
| Thrust (sea level) | 11,600 kgf |
| Propellants | LOX / RP-1 |
Clustered (x3) first-stage liquid rocket engine (LOX/RP-1, gas-generator cycle) in development for the Tronador II launch vehicle.
Clustered (x3) first-stage liquid rocket engine (LOX/RP-1, gas-generator cycle) in development for the Tronador II launch vehicle.
The MCA3 is a liquid-propellant (LOX/RP-1) rocket engine in development by VENG for a clustered (x3) first-stage configuration of the Tronador II launch vehicle, using a gas-generator feed cycle.
| Configuration | First stage, clustered (x3) |
|---|---|
| Thrust (vacuum) | 35,750 kgf |
| Propellants | LOX / RP-1 |
| Specific Impulse (vacuum) | 262 s |
| Feed System | Gas generator cycle |
Pressure-fed second-stage rocket engine (MMH/NTO) developed by VENG for the Tronador II launch vehicle.
Pressure-fed second-stage rocket engine (MMH/NTO) developed by VENG for the Tronador II launch vehicle.
The MES3K is a pressure-fed, hypergolic (MMH/NTO) liquid rocket engine developed by VENG for the second stage of the Tronador II launch vehicle programme.
| Stage | Second stage |
|---|---|
| Thrust (sea level) | 2,975 kgf |
| Propellants | MMH / NTO |
| Specific Impulse (vacuum) | 317 s |
| Feed System | Pressurized |
Pressure-fed liquid rocket engine (LOX/RP-1) developed by VENG.
Pressure-fed liquid rocket engine (LOX/RP-1) developed by VENG.
The MR500KB2 is a pressure-fed liquid rocket engine developed by VENG using a LOX/RP-1 propellant combination.
| Thrust (sea level) | 500 kgf |
|---|---|
| Propellants | LOX / RP-1 |
| Specific Impulse (sea level) | 223 s |
| Feed System | Pressurized |
Single-chamber bipropellant (LOX/RP-1) liquid rocket engine in development by VENG, suited to a second stage or clustered first-stage application.
Single-chamber bipropellant (LOX/RP-1) liquid rocket engine in development by VENG, suited to a second stage or clustered first-stage application.
The MT-B is a single-chamber bipropellant (LOX/RP-1) liquid rocket engine in development by VENG using an open-cycle gas-generator feed system. It is optimal for use as a second-stage engine or in a clustered first-stage configuration for the Tronador II launch vehicle family.
| Thrust (vacuum) | 4,280 kgf |
|---|---|
| Propellants | LOX / RP-1 |
| Specific Impulse (vacuum) | 330 s |
| Feed System | Open-cycle gas generator |
| Application | Second stage or clustered first-stage |
Pressure-fed liquid rocket engine (LOX/RP-1) developed by VENG.
Pressure-fed liquid rocket engine (LOX/RP-1) developed by VENG.
The RS-2 is a pressure-fed liquid rocket engine developed by VENG using a LOX/RP-1 propellant combination.
| Thrust (sea level) | 420 kgf |
|---|---|
| Propellants | LOX / RP-1 |
| Specific Impulse (sea level) | 264 s |
| Feed System | Pressurized |
No reviews yet — reviews come only from verified buyers after a completed request.
Write a review
We use cookies. Strictly necessary cookies keep the platform working. With your consent we also use Google Analytics to understand how the platform is used and improve it. We do not use advertising cookies. Cookie Policy · Privacy
Favorites are available to clients only. Sign in to your client cabinet or create a free account — it takes less than a minute.
How is your experience with the platform? Your message goes straight to our team.
Thank you! Your feedback has been sent to our team.
