The objective of the present paper is to prove the validity design and fully automatically operation of HPS, seeking to achieve its safety, low cost, and flexibility. In the stage of preliminary design, a coupling between experimental and theoretical work has been done, making use of available laboratory facilities and software packages (thermo-chemical calculation), to fully demonstrate all operating conditions. The HPS design includes the solid fuel grain configuration, essential operating parameters, oxidizer feed through control devices, measuring tools with calibration system, data recording and operating system. Commercial fuel materials as Polymethyl methacrylate (PMMA) and Polyethylene (PE) are used during experimental work to represent conventional generation fuel. Furthermore, new generation fuels as paraffin, beeswax, and paraffin with energetic additive metal (AL powder) are used. Gaseous oxygen is used as oxidizer. That may guide to design and fabricate high performance real rocket weapon or space propulsion system, targeting longer term storage and a propulsion system with available technology. The objective is extended to select appropriate ignition system (NiCr coil igniter) for laboratory firing of small-scale engine. One of the main problems (price, safety, available technology) of propulsion system today has been tackled. To that end, analysis has been established, to investigate the regression rate, solid fuel mass flow rate and combustion efficiency for each fuel grain group types.