Currently we have just completed our navigation and autopilot system, and moving on over to the rocket feeding system development. It will be determined by our mission and payload, which determines the thrust required to achieve the appropriate delta v for the rocket and spacecraft. Therefore the massflow rate from the feeding system to be developed soon will be a function of the thrust produced. We will start to build a Proof of Concept rocket propellant pump as part of the feeding system. There will be other components to be built that are associated to this system such as injector plate, ignition system, supply valves and pipes, etc.