¶ Demo A3
¶ All Demo A3 documentation
¶ Abreviations
- FTS : Flight Termination System
- MV : Main Valves
- GSE : Ground Support Element = Filling Station
- TC : Thrust Control
- CF : Cold Flow
- SFT : Static Fire Test
- VSFT : Vertical Static Fire Test
- LP : Launch Pad
¶ Requirements
Engine specifications¶ Sub Systems
n/a_class/demo_a3/engine_design){kind=link}
This page aims to describe the design phase of the bi-liquid rocket engine DEMO A3. DEMO A3 was engineered to be mounted on project Icarus' hopper, and therefore it will be the first engine from EPFL Rocket Team to be thrustable. Moreover, several new technologies like combustion chamber film cooling and spark igniter plug have been added to this engine.
Plumbing is an important part of a biliquid propulsion system. This page is about the design and implementation of this system for Demo A3 and the hopper.
Demo A3 is the first engine at ERT implementing Thrust Control. To allow this, the main valves have to achieve a precise control of the mass flow of both fuel and oxidizer. This page is about the hardware design of the valve themselves.
What is Thrust control ?
This is an electronic system who aims to an asked level of trust while maintaning the right stoichiometric proportion of the mixture (N2O + Ethanol).
The goal is to use it in the Icarus hopper.
What is FTS ?
FTS stands for Flight Termination System. Its purpose is to shut down the engine in the event of failure of all previous safety systems, in order to terminate the hopper's flight before it becomes uncontrollable.