How feasible would a rocket engine that ignited fuel in fast, high pressure pulses be. This type of engine would be especially applicable for low thrust burns such as for the raising of a small satellite into a higher orbit.
The engine could use bi-propellants such as methane/oxygen and an igniter or hypergolics or a mono-propellant sprayed onto a catalyst. Such a system would inject a spray of propellant into the combustion chamber followed by the closing of the propellant valves leading into the chamber and then the ignition of the propellant. The hot gas would rush out of the chamber in a high speed pulse and then the cycle would repeat.
The advantages I can see with such a system are be:
Very high possible chamber pressures and thus high exhaust velocity and ISP without heavy high propellant tanks or the impracticability of tiny high pressure gas turbines/pumps because the propellant lines into the chamber would be sealed off before each pulse cycle.
The required chamber pressure can be easily changed by increasing/decreasing the throat area and the strength of the combustion chamber walls without the need for modifying the rest of the propulsion system(Tanks, propellant feed lines etc.).
EDIT: A simple diagram for clarification