|  | 
         
          | 
               
                | 
                       
                      | Hypertek 
 HyperTEK is a modular, hybrid propellant rocket motor 
                        system that uses readily available nitrous oxide (N2O) 
                        and thermoplastic fuel grains. The HyperTEK system uses 
                        the patented Kline valve to control the flow of oxidizer. 
                        This unique design allows for safe, remote filling of 
                        the oxidizer tank on the pad. Thousands of systems have 
                        been in use around the world since it's design by eAc 
                        in 1994. Designed primarily for use in launching small 
                        experimental payloads by universities, colleges, research 
                        institutes and sport rocketry enthusiasts, the system 
                        is also intended to be a technology demonstrator for hybrid 
                        propulsion technology. eAc has licensed the manufacturing 
                        and distribution of the HyperTEK Hybrid Propulsion System 
                        to Cesaroni 
                        Technology Incorporated (CTI).
 
 Extensive research and development by CTI and eAc has 
                        refined the system yielding a high tech, low cost rocket 
                        motor alternative to the current solid propellant rocket 
                        motor. Hybrid motors have several safety advantages over 
                        solids. The fuel and oxidizer are isolated from each other 
                        until just before ignition, thus eliminating the requirement 
                        for a low explosive permit during transportation and storage 
                        of rocket motors. The HyperTEK hybrid propulsion system 
                        uses a remote fill/fire launch system as well as 100% 
                        pyrotechnic free ignition system.
 
 The HyperTEK flight motor consists of three major parts: 
                        the oxidizer tank, the injector bell and the fuel grain. 
                        The fuel grain is molded from thermoplastic and has an 
                        insert-molded silica/phenolic nozzle. This monolithic 
                        grain functions as both the fuel and the combustion chamber. 
                        Incorporating the fuel, nozzle and motor case into one 
                        injection molded component has eliminated the complicated 
                        assembly of a reloadable system. The fuel grain simply 
                        screws onto the injector bell prior to flight and the 
                        spent fuel grain is unscrewed and discarded of after each 
                        flight. The injector bell has field interchangeable injector 
                        orifices for tailoring the time/thrust profile to the 
                        needs of the rocket. Potential applications include small 
                        sounding rockets, RATO boosters and more.
 |  |    |  |   
          |  |  |  |  |