Propulsion Services
Since our beginnings, one of our main areas of technological development has been the area of liquid propulsion, mainly oriented to the development of propellants for launch vehicles and also small propellants for attitude control of launchers and potential use in the satellite industry.
MT-B ENGINE
The MT-B is a bipropellant liquid rocket engine with a single regeneratively cooled thrust chamber, powered by an open-cycle gas generator. It was developed as the propulsion system for the second stage of the Tronador TII-250 vehicle. The thrust chamber was manufactured using a combination of additive manufacturing and electroforming technologies.
|
USE |
E2 of TII-250 (x1)
|
|
THRUST TO ADAPTED NOZZLE
|
4280 Kgf
|
|
PROPELLENTS |
LOX/RP1
|
|
SPECIFIC VACUUM THRUST
|
366 S |
|
FEED SYSTEM |
GAS GENERATOR CYCLE |
launch vehicle engines —
Regarding higher thrust liquid propellants, we have an extensive experience of more than a decade in the development of Hydrazine/Nitric Acid and LOx/Kerosene engines for launcher prototypes, having as main milestones the design, manufacturing, testing and integration in the TI, T4000, VEx 1A, Vex1B and VEx5A launcher prototypes.
As a reference, the VEx5A first stage engine is shown, the largest propellant developed to date.
Today we are leading as prime contractor in the design of the thrusters for the Tronador II launcher series, taking care of the complete propulsion value cycle: from the definition of requirements, through design, simulation, manufacturing, testing, qualification and integration in the final vehicle.
This experience allows us to adapt to any propulsion solution required by the customer, both for launchers, satellites and spacecraft in general.
MES3K ENGINE
2nd stage
|
USE |
E1 of VEX1 (x1)
E2 of VEX5A (x1)
E2 of TII-250 (x1) |
|
THRUST AT SL |
2975 Kgf |
|
PROPELLENTS |
MMH/NTO |
|
SPECIFIC IMPULSE AT SL |
317 S |
|
FEED SYSTEM |
PRESSURIZED |
MCA3 ENGINE
1ST STAGE
|
USE |
E1 of TII-250 (x3) |
|
THRUST TO ADAPTED NOZZLE |
35750 Kgf |
|
PROPELLANTS |
LOX/RP1 |
|
SPECIFIC IMPULSE AT SL |
262 S |
|
FEED SYSTEM |
GAS GENERATOR CYCLE
|
Regarding small thrusters, we have the heritage of having participated in the development of prototypes of the order of 1, 5 N thrust, monopropellant, at laboratory level, having verified the development capacity of this type of thrusters, being able to adapt to the needs of satellite customers and the space industry in general.
Access to Space Brochure
1.5 N THRUST MONOPROPELLANT PROPELLER —
Monopropellant engines base their operation on the catalytic decomposition of the fuel, which generates heat and gasification of the fuel. The gases produced are then expanded in a nozzle to produce thrust.
|
THRUST |
1,5 N @ (400psia)
|
|
PROPELLENT |
Monopropellant (Hydrazine) |
|
TYPE OF VALVE |
Double solenoid, double seal |
|
CATALYZER |
Shell 405 |
|
SPECIFIC IMPULSE |
220 sec @ 400psia |
|
MAXIMUM WEIGHT |
0,5 kg |
Dimensions
|
LENGTH |
< 195 mm. |
|
HEIGHT |
< 55 mm. |
|
WIDTH |
< 45 mm. |
MCA2 ENGINE
1ST STAGE
|
USE |
E1 of VEX5 (x1) |
|
THRUST AT SL |
11600 Kgf |
|
PROPELLANTS |
LOX/RP-1 |
|
SPECIFIC IMPULSE AT SL |
237 S |
|
FEED SYSTEM |
PRESSURIZED |