Executor (rocket engine)
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 ARCA Executor (shown) | |
| Country of origin | Romania |
|---|---|
| Manufacturer | ARCA |
| Liquid-fuel engine | |
| Propellant | LOX / Kerosene |
| Cycle | gas-generator |
| Performance | |
| Thrust, vacuum | 260 kN (57,300 lbf) |
| Thrust, sea-level | 220 kN (48,500 lbf) |
| Chamber pressure | 4.3 MPa |
| Specific impulse, vacuum | 295s |
| Specific impulse, sea-level | 270s |
| Dimensions | |
| Diameter | 720mm |
| Dry mass | 260kg |
Executor is a rocket engine developed by ARCA[1] for use on its Haas rocket series and on IAR 111 Excelsior supersonic airplane. Executor uses kerosene[2] and liquid oxygen as propellants in a gas-generator power cycle.
The injector of Executor is of the pintle type that was first used in the Apollo Program for the lunar module landing engine.
Propellants are fed via a single shaft, dual inducer-impeller turbo-pump. The turbine exhaust gases are used for attitude control of the Haas 2 rocket.
Two versions of the Executor are in development. The Executor engine for the first stage of the Haas 2B and Super Haas launchers and for the IAR-111 Excelsior airplane. The second variant is the Executor Plus engine that it uses a larger exhaust nozzle optimized for vacuum operation. The Executor Plus is used on the Haas 2 air-launched rocket and on the second stage of the Super Haas rocket.[3]
Engine description
Executor, uses an inexpensive, expendable, ablatively cooled silica-phenolic and carbon fiber composite nozzle, and produce 260 kN of thrust. The engine's ablative nozzle is designed for a 180-second run. The internal structure of the engine is made of silica-phenolic composite, while the outer structure is carbon-epoxy. The structure thickness varies from 10mm to 30mm. Beside the ablative cooling, the engine is using a kerosene film cooling method.[4]